Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules 16603 

34Public Law 105–277, 112 Stat. 2681 (1998). 

National Credit Union Administration, 

Office of Information and Regulatory 

Affairs, Washington, DC 20503. 

C. Executive Order 13132 

Executive Order 13132 encourages 

independent regulatory agencies to 

consider the impact of their actions on 

state and local interests. NCUA, an 

independent regulatory agency, as 

defined in 44 U.S.C. 3502(5), voluntarily 

complies with the executive order to 

adhere to fundamental federalism 

principles. Because the fixed assets 

regulation applies only to FCUs, the 

2015 proposal 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. As such, NCUA 

has determined that this rule does not 

constitute a policy that has federalism 

implications for purposes of the 

executive order. 

D. Assessment of Federal Regulations 

and Policies on Families 

NCUA has determined that this rule 

will not affect family well-being within 

the meaning of Section 654 of the 

Treasury and General Government 

Appropriations Act of 1999.34

List of Subjects in 12 CFR Part 701 

Credit unions, Reporting and 

recordkeeping requirements. 

By the National Credit Union 

Administration Board, on March 19, 2015. 

Gerard Poliquin, 

Secretary of the Board. 

For the reasons stated above, NCUA 

proposes to amend 12 CFR 701.36 as 

follows: 

PART 701—ORGANIZATION AND 

OPERATION OF FEDERAL CREDIT 

■ 1. The authority for part 701 

continues to read as follows: 

Authority: 12 U.S.C. 1752(5), 1757, 1765, 

1757, 1758, 1759, 1761a, 1761b, 1766, 1767, 

1782, 1784, 1786, 1787, 1789. Section 701.6 

is also authorized by 15 U.S.C. 3717. Section 

701.31 is also authorized by 15 U.S.C. 1601 

et seq.; 42 U.S.C. 1981 and 3601–3610. 

Section 701.35 is also authorized by 42 

U.S.C. 4311–4312. 

■ 2. In § 701.36 revise the section 

heading and paragraph (a) to read as 

follows: 

§ 701.36 Federal credit union occupancy, 

planning, and disposal of acquired and 

abandoned premises. 

(a) Scope. Section 107(4) of the 

Federal Credit Union Act (12 U.S.C. 

1757(4)) authorizes a federal credit 

union to purchase, hold, and dispose of 

property necessary or incidental to its 

operations. This section interprets and 

implements that provision by 

establishing occupancy, planning, and 

disposal requirements for acquired and 

abandoned premises, and by prohibiting 

certain transactions. 

This section applies only to federal 

credit unions. 

* * * * * 

■ 3. Revise § 701.36 paragraph (b) by 

removing the following definitions: 

‘‘fixed assets’’, ‘‘furniture, fixtures, and 

equipment’’, ‘‘investments in fixed 

assets’’, ‘‘retained earnings’’, and 

‘‘shares’’. 

■ 4. Remove § 701.36 paragraph (c). 

■ 5. Revise § 701.36 paragraph (d)(2) to 

read as follows: 

(d) * * * 

(2) If a federal credit union acquires 

premises for future expansion, 

including unimproved land or 

unimproved real property, it must 

partially occupy them within a 

reasonable period, but no later than six 

years after the date of acquisition. 

NCUA may waive the partial occupation 

requirements. To seek a waiver, a 

federal credit union must submit a 

written request to its Regional Office 

and fully explain why it needs the 

waiver. The Regional Director will 

provide the federal credit union a 

written response, either approving or 

disapproving the request. The Regional 

Director’s decision will be based on 

safety and soundness considerations. 

* * * * * 

■ 6. In § 701.36 redesignate paragraph 

(d) as paragraph (c) and paragraph (e) as 

paragraph (d). 

[FR Doc. 2015–06816 Filed 3–27–15; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0674; Directorate 

Identifier 2014–SW–019–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2014–05– 

06 for certain Eurocopter Deutschland 

GmbH (ECD) (now Airbus Helicopters 

Deutschland GmbH) Model EC135 and 

MBB–BK 117 C–2 helicopters to correct 

an error. AD 2014–05–06 currently 

requires inspecting the flight-control 

bearings repetitively, replacing any 

loose bearing with an airworthy flightcontrol bearing, and installing bushings 

and washers. This proposed AD would 

require the same actions. This proposed 

AD results from the discovery of an 

error in the compliance time for AD 

2014–05–06. These proposed actions are 

intended to prevent the affected control 

lever from shifting, contacting the 

helicopter structure, and reducing 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by May 29, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

European Aviation Safety Agency 


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(EASA) AD, the economic evaluation, 

any comments received and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this proposed AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–0674. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email matthew.fuller@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On February 20, 2014, we issued AD 

2014–05–06, Amendment 39–17779 (79 

FR 13196, March 10, 2014), for certain 

ECD (now Airbus Helicopters 

Deutschland GmbH) Model EC135 and 

MBB–BK 117 C–2 helicopters. AD 

2014–05–06 requires inspecting the 

flight-control bearings repetitively, 

replacing any loose bearing with an 

airworthy flight-control bearing, and 

installing bushings and washers. AD 

2014–05–06 was prompted by the 

discovery of loose flight control bearings 

because of incorrect installation. This 

condition, if not corrected, could result 

in the affected control lever shifting, 

contacting the helicopter structure, and 

reducing control of the helicopter. 

Actions Since AD 2014–05–06 Was 

Issued 

Since we issued AD 2014–05–06 (79 

FR 13196, March 10, 2014), we 

discovered an error regarding the 

compliance time for certain model 

helicopters. Paragraph (e)(1)(i) should 

have required that certain actions be 

accomplished within the next 100 hours 

time-in-service or at the next annual 

inspection, whichever occurs first. 

However, we omitted the word ‘‘first’’ 

from that sentence, which changes the 

meaning of the required compliance 

time. 

Also since we issued AD 2014–05–06, 

ECD changed its name to Airbus 

Helicopters Deutschland GmbH. This 

proposed AD reflects that change and 

updates the contact information to 

obtain service documentation. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

ECD, now called Airbus Helicopters, 

has issued Alert Service Bulletin (ASB) 

MBB BK117 C–2–67A–010, Revision 3, 

dated February 8, 2010, and ASB 

EC135–67A–019, Revision 3, dated 

December 16, 2009. These ASBs specify: 

• Within the next 50 flight hours 

(FHs), inspecting the affected bearings 

and, if necessary, rebonding any 

affected bearings or replacing the lever 

assembly. 

• Within 12 months, retrofitting 

bushings and washers on the levers to 

prevent movement of the bearings. 

• After the retrofit, repeating the 

inspection every 800 FHs or 36 months 

for the Model EC135 helicopters, 

whichever comes first, and 600 FHs or 

24 months, whichever comes first, for 

the Model MBB–BK 117 C–2 

helicopters. 

EASA classified these ASBs as 

mandatory and issued AD No. 2010– 

0058 to ensure the continued 

airworthiness of these helicopters. 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 of 

this NPRM. 

Proposed AD Requirements 

For Airbus Model EC135 P1, P2, P2+, 

T1, T2, and T2+ helicopters this 

proposed AD would require: 

• Within the next 100 hours time-inservice (TIS) or at the next annual 

inspection, whichever occurs first, 

modifying the left-hand (LH) and righthand (RH) guidance units and the cyclic 

shaft by installing bushings and washers 

to prevent shifting of the bearings in the 

axial direction. 

• At intervals not to exceed 800 hours 

TIS or 36 months, whichever occurs 

first, inspecting the bearings in the LH 

guidance unit, RH guidance unit, cyclic 

control, upper guidance unit, and linear 

voltage differential transducer plate for 

play. If any bearing is loose, replacing 

the affected bearing with an airworthy 

bearing. 

For Model MBB–BK 117 C–2 

helicopters, this proposed AD would 

require: 

• Within the next 100 hours TIS or at 

the next annual inspection, whichever 

occurs first, modifying the LH and RH 

guidance units and the lateral control 

lever by installing bushings and washers 

to prevent shifting of the bearings in the 

axial direction. 

• At intervals not to exceed 600 hours 

TIS or 24 months, whichever occurs 

first, inspecting the bearings in the RH 

guidance unit, LH guidance unit, and 

lateral control guidance unit for play. If 

any bearing is loose, replacing the 

affected bearing with an airworthy 

bearing. 

Differences Between This Proposed AD 

and the EASA AD 

Differences between this proposed AD 

and the EASA AD are: 

• The EASA AD is applicable to the 

EC 635 helicopter, whereas this 

proposed AD is not because the EC 635 

helicopter is not type certificated in the 

U.S. 

• The EASA AD requires an initial 

inspection within 50 flight hours or one 


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month, whichever occurs first after May 

31, 2008, and a modification within the 

next 12 months. This proposed AD 

would require the modification within 

100 hours TIS or at the next annual 

inspection, whichever occurs first, and 

no inspection until after the 

modification has been accomplished. 

• The EASA AD applies to all EC135 

and MBB–BK 117 C–2 helicopters, 

while this proposed AD would apply to 

certain serial-numbered Model EC135 

and Model MBB–BK 117 C–2 

helicopters, as recommended by the 

appropriate ECD ASB. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 175 Model EC135 and 112 

Model MBB–BK 117 C–2 helicopters of 

U.S. Registry and that labor costs would 

average $85 per work-hour. Based on 

these estimates, we expect the following 

costs: 

• For EC135 helicopters, it would 

take about 32 work-hours to perform the 

modification. Parts would cost about 

$312. The total cost for the modification 

would be about $3,032 per helicopter 

and $530,600 for the U.S. operator fleet. 

The repetitive inspections would 

require 6.5 work-hours for a cost of 

about $553 per helicopter and about 

$96,775 for the fleet per inspection 

cycle. 

• For MBB–BK 117 C–2 helicopters, it 

would take about 32 work-hours to 

perform the modification. Parts would 

cost about $396. The total cost for the 

modification would be $3,116 per 

helicopter and $348,992 for the U.S. 

operator fleet. The cost for the repetitive 

inspections thereafter would be about 

$85 per helicopter and $9,520 for the 

fleet per inspection cycle. 

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, 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 

removing Airworthiness Directive (AD) 

2014–05–06, Amendment 39–17779 (79 

FR 13196, March 10, 2014), and adding 

the following new AD: 

Airbus Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH): Docket No. FAA–2015–0674; 

Directorate Identifier 2014–SW–019–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: 

(1) Model EC135 P1, P2, P2+, T1, T2, and 

T2+ helicopters, serial number (S/N) 0005 

through 00829, with a tail rotor control lever, 

part number (P/N) L672M2802205 or 

L672M1012212; cyclic control lever, P/N 

L671M1005250; collective control lever 

assembly, P/N L671M2020108; or collective 

control plate, P/N L671M5040207; installed; 

and 

(2) Model MBB–BK 117 C–2 helicopters, S/ 

N 9004 through 9310, with a tail rotor control 

lever assembly, P/N B672M1007101 or 

B672M1807101; tail rotor control lever, P/N 

B672M1002202 or L672M2802205; or lateral 

control lever assembly, P/N B670M1008101, 

installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

incorrectly installed flight control bearings. 

This condition could cause the affected 

control lever to shift and contact the 

helicopter structure, resulting in reduced 

control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2014–05–06, 

Amendment 39–17779 (79 FR 13196, March 

10, 2014). 

(d) Comments Due Date 

We must receive comments by May 29, 

2015. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) For Model EC135 P1, P2, P2+, T1, T2, 

and T2+ helicopters: 

(i) Within the next 100 hours timeinservice (TIS) or at the next annual 

inspection, whichever occurs first, modify 

the left-hand (LH) and right-hand (RH) 

guidance units and the cyclic shaft by 

installing bushings and washers to prevent 

shifting of the bearings in the axial direction 

as follows: 

(A) Remove and disassemble the LH 

guidance unit and install a bushing, P/N 

L672M1012260, between the bearing block 

and the lever of the LH guidance unit as 

depicted in Detail A of Figure 5 of Eurocopter 

Alert Service Bulletin EC135–67A–019, 

Revision 3, dated December 16, 2009 (EC135 

ASB). 

(B) For helicopters without a yaw brake, 

remove and disassemble the RH guidance 

unit and install a bushing, P/N 

L672M1012260, between the bearing block 

and the lever as depicted in Detail B of 

Figure 5 of EC135 ASB. 

(C) Remove and disassemble the cyclic 

shaft and install a washer, P/N 

L671M1005260, between the bearing block 

and the lever as depicted in Detail C of 

Figure 6 of EC135 ASB. 

(D) Remove the collective control rod from 

the bellcrank and install a washer, P/N 

L221M1042208, on each side of the collective 

control rod and bellcrank as depicted in 

Detail D of Figure 6 of EC135 ASB. 

(E) At intervals not to exceed 800 hours 

TIS or 36 months, whichever occurs first, 

inspect the bearings in the LH guidance unit, 

RH guidance unit, cyclic control, upper 

guidance unit, and linear voltage differential 

transducer plate for play. If any bearing is 


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loose, replace the affected bearing with an 

airworthy bearing. 

(2) For Model MBB–BK 117 C–2 

helicopters: 

(i) Within the next 100 hours TIS or at the 

next annual inspection, whichever occurs 

first, modify the LH and RH guidance units 

and the lateral control lever by installing 

bushings and washers to prevent shifting of 

the bearings in the axial direction as follows: 

(A) Remove and disassemble the RH 

guidance unit and install a bushing, P/N 

L672M1012260, between the lever and the 

bracket as depicted in Detail B of Figure 4 of 

Eurocopter Alert Service Bulletin MBB 

BK117 C–2–67A–010, Revision 3, dated 

February 8, 2010 (BK117 ASB). Remove and 

disassemble the LH guidance unit and install 

a bushing, P/N L672M1012260, between the 

lever and the bracket as depicted in Detail C 

of Figure 4 of BK117 ASB. 

(B) Remove the lateral control lever and 

install new bushings in accordance with the 

Accomplishment Instructions, paragraphs 

3.C(9)(a) through 3.C(9)(g), of BK 117 ASB. 

(C) Identify the modified lever assembly by 

writing ‘‘MBB BK117 C–2–67A–010’’ on the 

lever with permanent marking pen and 

protect with a single layer of lacquer (CM 421 

or equivalent). 

(D) Apply corrosion preventive paste (CM 

518 or equivalent) on the shank of the screws 

and install airworthy parts as depicted in 

Figure 5 of BK117 ASB. 

(E) At intervals not to exceed 600 hours 

TIS or 24 months, whichever occurs first, 

inspect the bearings in the RH guidance unit, 

LH guidance unit, and lateral control 

guidance unit for play. If any bearing is loose, 

replace the affected bearing with an 

airworthy bearing. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matthew.fuller@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0058, dated March 30, 2010. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2015–0674. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710, Main Rotor Control. 

Issued in Fort Worth, Texas, on March 18, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–06806 Filed 3–27–15; 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] 

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 supersede 

Airworthiness Directive (AD) 2007–16– 

08, which applies 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 

currently requires repetitive inspections 

for cracking of the station 800 frame 

assembly, and repair if necessary. Since 

we issued AD 2007–16–08, we have 

received additional 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. This proposed AD 

would expand the inspection area. We 

are proposing 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: We must receive comments on 

this proposed AD by May 14, 2015. 

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 proposed 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.gov by 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 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 proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0498; Directorate Identifier 

2014–NM–152–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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS