19514 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 

widespread fatigue damage (WFD). We are 

issuing this AD to detect and correct fatigue 

cracking around certain fastener locations 

that could cause multiple window corner 

skin cracks, which could result in rapid 

decompression and consequent reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Repair 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1351, dated 

July 8, 2015: Do an external high frequency 

eddy current (HFEC) inspection for cracking 

of the skin around the fastener locations at 

the upper forward and lower aft corners of 

each window between station (STA) 360 and 

STA 540, as applicable, and at the lower 

forward and upper aft corners of each 

window between STA 727 and STA 887, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1351, dated July 8, 2015. Repeat the 

inspection thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1351, 

dated July 8, 2015. If any crack is found 

during any inspection, repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(h) Exception to the Service Bulletin 

Specifications 

Although Boeing Alert Service Bulletin 

737–53A1351, dated July 8, 2015, specifies to 

contact Boeing for repair instructions, and 

specifies that action as ‘‘RC’’ (Required for 

Compliance), this AD requires repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(i) 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 (j)(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) Except as required by paragraph (h) of 

this AD: For service information that 

contains steps that are labeled as RC, the 

provisions of paragraphs (i)(4)(i) and (i)(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. 

(j) Related Information 

(1) For more information about this AD, 

contact Jason Deutschman, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6595; fax: 425–917–6590; email: 

jason.deutschman@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. 

You may view the 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. 

Issued in Renton, Washington, on March 

24, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07577 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–2016–5041; Directorate 

Identifier 2015–NM–102–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–8 and 

747–8F series airplanes. This proposed 

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. This proposed AD would 

require removing aluminum 

transmission aft bearing plate 

assemblies from the flap track and 

installing titanium transmission aft 

bearing plate assemblies to the flap 

track. We are proposing 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. 

DATES: We must receive comments on 

this proposed AD by May 20, 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 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.gov by searching for 

and locating Docket No. FAA–2016– 

5041. 

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– 


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Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 19515 

5041; 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: 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: 

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– 

2016–5041; Directorate Identifier 2015– 

NM–102–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 have received 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. These types of load 

cases can cause a flap transmission 

torque brake to engage, which will then 

cause additional loading on the 

transmission aft bearing plate 

assemblies common to that flap. This 

could cause damage to the transmission 

aft bearing plate assemblies. This 

condition, if not corrected, could result 

in transmission aft bearing plate 

assemblies working incorrectly or 

departure of the flap from the airplane, 

which could result in loss of 

controllability of the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–57A2348, dated June 12, 

2015. The service information describes 

procedures for removing the aluminum 

transmission aft bearing plate assembly 

from the flap track and installing a new 

titanium transmission aft bearing plate 

assembly to the flap track. 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 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 11 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replacement .......................... 114 work-hours × $85 per hour = $9,690 .............................. $48,682 $58,372 $642,092 

According to the manufacturer, all of 

the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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, 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: 


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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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