19516 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 

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): 

The Boeing Company: Docket No. FAA– 

2016–5041; Directorate Identifier 2015– 

NM–102–AD. 

(a) Comments Due Date 

We must receive comments by May 20, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–8 and 747–8F series airplanes, 

certified in any category, as identified in 

Boeing Alert Service Bulletin 747–57A2348, 

dated June 12, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report that 

static strength analysis has shown that the 

aluminum transmission aft bearing plate 

assemblies have inadequate structural 

strength for one or more of the required load 

cases, including cases for drive system jam, 

flap skew, and structural damage tolerance. 

Inadequate structural strength can result in 

damage to the transmission aft bearing plate 

assemblies. We are issuing this AD to prevent 

inadequate structural strength of 

transmission aft bearing plate assemblies. 

This condition could result in damaged 

transmission aft bearing plate assemblies, 

which could result in incorrect operation and 

departure of the flap from the airplane and 

consequent loss of controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Within 48 months after the effective date 

of this AD: Remove aluminum transmission 

aft bearing plate assemblies from the flap 

track and install new titanium transmission 

aft bearing plate assemblies to the flap track, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2348, dated June 12, 2015. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (i)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (h)(4)(i) and (h)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(i) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6432; fax: 425– 

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

(2) 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. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on March 

24, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07578 Filed 4–4–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4123; Directorate 

Identifier 2016–NE–06–AD] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

International Aero Engines AG (IAE) 

V2522–A5, V2524–A5, V2525–D5, 

V2527–A5, V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, and V2533–A5 

turbofan engines. This proposed AD was 

prompted by the fracture of the highpressure turbine (HPT) stage 2 hub 

during flight, which resulted in an inflight shutdown (IFSD), undercowl fire, 

and smoke in the cabin. This proposed 

AD would require inspecting the HPT 

stage 1 hub and HPT stage 2 hub, and, 

if necessary, their replacement with 

parts that are eligible for installation. 

We are proposing this AD to prevent 

failure of the HPT stage 1 or HPT stage 

2 hubs, which could result in 

uncontained HPT blade release, damage 

to the engine, and damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by June 6, 2016. 

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. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building 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 NPRM, contact International Aero 

Engines AG, 400 Main Street, East 

Hartford, CT 06118; phone: 860–368– 

3700; fax: 860–368–4600; email: 

iaeinfo@iaev2500.com; Internet: https:// 

www.iaeworld.com. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA. For 


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Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 19517 

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–2016– 

4123 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 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 after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7772; fax: 781–238–7199; 

email: brian.kierstead@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2016–4123; Directorate Identifier 2016– 

NE–06–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We received a report of an engine 

IFSD and subsequent undercowl fire on 

an IAE V2527–A5 turbofan engine 

during a revenue flight of an Airbus 

A320 airplane in September 2014. The 

subsequent investigation of this event 

determined that it was caused by a 

manufacturing defect in the HPT stage 

2 hub that resulted in fracture and 

failure of the HPT stage 2 hub. The 

event involved release of a fir tree lug 

and two HPT stage 2 blades. IAE also 

identified a similar manufacturing 

defect on the HPT stage 1 hub. This 

condition, if not corrected, could result 

in uncontained HPT blade release, 

damage to the engine, and damage to the 

airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed IAE Non-Modification 

Service Bulletin (NMSB) No. V2500– 

ENG–72–0661, Revision No. 1, dated 

February 5, 2016. The NMSB describes 

procedures for inspecting the HPT stage 

1 and stage 2 hubs. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

FAA’s Determination 

We are proposing this AD 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 Requirements 

This proposed AD would require 

inspecting the engine HPT stage 1 hub 

and HPT stage 2 hub, and, if necessary, 

their replacement with parts eligible for 

installation. 

Costs of Compliance 

We estimate that this proposed AD 

affects 668 engines with 947 hubs 

installed on airplanes of U.S. registry. 

Some of the 668 engines have two hubs 

installed. We estimate that it would take 

about 8 hours per hub to perform the 

piece-part inspection. The average labor 

rate is $85 per hour. We estimate that 

568 hubs will require replacement. We 

estimate the pro-rated cost to replace an 

HPT stage 1 hub to be $50,271 and the 

pro-rated cost to replace an HPT stage 

2 hub to be $40,063. Based on these 

figures, we estimate the cost of this 

proposed AD on U.S. operators to be 

$26,298,816. 

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 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the 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. 

The 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 

■ 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): 

International Aero Engines AG: Docket No. 

FAA–2016–4123; Directorate Identifier 

2016–NE–06–AD. 

(a) Comments Due Date 

We must receive comments by June 6, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to International Aero 

Engines AG (IAE) V2522–A5, V2524–A5, 


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19518 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 

V2525–D5, V2527–A5, V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, and 

V2533–A5, engines with either of the 

following installed: 

(1) High-pressure turbine (HPT) stage 1 

hub, part number (P/N) 2A5001, with a serial 

number (S/N) listed in Table 1, Appendix A, 

of IAE Non-Modification Service Bulletin 

(NMSB) No. V2500–ENG–72–0661, Revision 

1, dated February 5, 2016; or 

(2) HPT stage 2 hub, P/N 2A4802, with an 

S/N listed in Table 2, Appendix A, of IAE 

NMSB No. V2500–ENG–72–0661, Revision 1, 

dated February 5, 2016. 

(d) Unsafe Condition 

This AD was prompted by the fracture of 

the HPT stage 2 hub during flight, which 

resulted in an in-flight shutdown, undercowl 

fire, and smoke in the cabin. We are issuing 

this AD to prevent failure of the HPT stage 

1 or HPT stage 2 hubs, which could result in 

uncontained HPT blade release, damage to 

the engine, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Inspect the HPT stage 1 hub, P/N 

2A5001, and HPT stage 2 hub, P/N 2A4802, 

at the next shop visit or as follows, 

whichever comes first: 

(i) For hubs with 0 to 7,000 CSN, before 

accumulating 13,000 CSN; 

(ii) For hubs with 7,001 to 11,000 CSN, 

within 6,000 cycles from the effective date of 

this AD or before accumulating 15,000 CSN, 

whichever occurs first; 

(iii) For hubs with 11,001 to 15,500 CSN, 

within 4,000 cycles from the effective date of 

this AD or before accumulating 17,000 CSN, 

whichever occurs first; 

(iv) For hubs with 15,501 CSN or greater, 

within 1,500 cycles from the effective date of 

this AD. 

(2) Use Accomplishment Instructions, 

paragraphs 2.A., 2.C., and 2.D., of IAE NMSB 

No. V2500–ENG–72–0661, Revision 1, dated 

February 5, 2016, to inspect the HPT stage 1 

hub, P/N 2A5001. 

(3) Use Accomplishment Instructions, 

paragraphs 2.E., 2.G., and 2H., of IAE NMSB 

No. V2500–ENG–72–0661, to inspect the 

HPT stage 2 hub, P/N 2A4802. 

(4) Remove from service any HPT stage 1 

hub, P/N 2A5001, or HPT stage 2 hub, P/N 

2A4802, that fail the inspections required by 

paragraphs (e)(2) and (e)(3) of this AD, and 

replace with a part that is eligible for 

installation. 

(f) Definition 

For the purpose of this AD, a ‘‘shop visit’’ 

is the induction of an engine into the shop 

for maintenance involving the separation of 

pairs of major mating engine flanges, except 

that the separation of engine flanges solely 

for the purposes of transportation without 

subsequent engine maintenance does not 

constitute an engine shop visit. 

(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 Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7772; fax: 781–238–7199; email: 

brian.kierstead@faa.gov. 

(2) For service information identified in 

this proposed AD, contact International Aero 

Engines AG, 400 Main Street, East Hartford, 

CT 06118; phone: 860–368–3700; fax: 860– 

368–4600; email: iaeinfo@iaev2500.com; 

Internet: https://www.iaeworld.com. 

(3) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA. For 

information on the availability of this 

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

Issued in Burlington, Massachusetts, on 

March 24, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–07579 Filed 4–4–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Office of Workers’ Compensation 

Programs 

20 CFR Part 30 

RIN 1240–AA08 

Claims for Compensation Under the 

Energy Employees Occupational 

Illness Compensation Program Act 

AGENCY: Office of Workers’ 

Compensation Programs, Department of 

Labor. 

ACTION: Notice of proposed rulemaking; 

reopening of comment period. 

SUMMARY: The Department of Labor is 

reopening and extending the comment 

period for the notice of proposed 

rulemaking it published on November 

18, 2015 (80 FR 72296). The Department 

originally allowed a 60-day comment 

period that was scheduled to close on 

January 19, 2016, but on that date 

extended the comment period another 

30 days through February 18, 2016 (81 

FR 2787). This notice indicates that the 

comment period is being reopened as of 

April 5, 2016 and extended for an 

additional period. The comment period 

for the information collection 

requirements in the proposed rule 

ended on December 18, 2015, and that 

period is not being reopened. 

DATES: The comment period for the 

notice of proposed rulemaking 

published on November 18, 2015 (80 FR 

72296) and extended at 81 FR 2787 

(January 19, 2016) is reopened. The 

Department will accept written 

comments on the notice of proposed 

rulemaking from interested parties that 

are submitted from April 5, 2016 

through May 9, 2016. 

ADDRESSES: Parties may submit 

comments on the regulations in the 

proposed rule, identified by Regulatory 

Information Number (RIN) 1240–AA08, 

by any ONE of the following methods: 

Federal e-Rulemaking Portal: The 

Internet address to submit comments on 

the regulations in the proposed rule is 

www.regulations.gov. Follow the Web 

site instructions for submitting 

comments. Comments will also be 

available for public inspection on the 

Web site. 

Mail or Hand Delivery: Submit written 

comments by mail to Rachel P. Leiton, 

Director, Division of Energy Employees 

Occupational Illness Compensation, 

Office of Workers’ Compensation 

Programs, U.S. Department of Labor, 

Room C–3321, 200 Constitution Avenue 

NW., Washington, DC 20210. The 

Department will only consider mailed 

comments that have been postmarked 

by the U.S. Postal Service or other 

delivery service on or before the 

deadline for comments. 

Instructions: All comments must cite 

RIN 1240–AA08 that has been assigned 

to this rulemaking. Receipt of any 

comments, whether by Internet, mail or 

hand delivery, will not be 

acknowledged. 

FOR FURTHER INFORMATION CONTACT: 

Rachel P. Leiton, Director, Division of 

Energy Employees Occupational Illness 

Compensation, Office of Workers’ 

Compensation Programs, U.S. 

Department of Labor, Room C–3321, 200 

Constitution Avenue NW., Washington, 

DC 20210, Telephone: 202–693–0081 

(this is not a toll-free number). 

Individuals with hearing or speech 

impairments may access this telephone 

number via TTY by calling the toll-free 

Federal Information Relay Service at 1– 

800–877–8339. 

SUPPLEMENTARY INFORMATION: In 

response to requests from members of 

the public, the Department has decided 

to reopen the public comment period for 

the notice of proposed rulemaking it 

published on November 18, 2015 (80 FR 

72296). The Department originally 

allowed a 60-day comment period that 

was scheduled to close on January 19, 

2016, but on that date extended the 

comment period another 30 days 

through February 18, 2016 (81 FR 2787). 

The comment period is being reopened 

as of April 5, 2016 and extended 

through May 9, 2016. The comment 


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