39394 Federal Register / Vol. 80, No. 131 / Thursday, July 9, 2015 / Proposed Rules 

(a) Comments Due Date 

We must receive comments by August 24, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes, certificated in any 

category, as identified in Boeing Special 

Attention Service Bulletin 777–54–0035, 

dated October 30, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of fire 

and smoke at the engine aft pylon area 

resulting from fuel leakage caused by a 

damaged O-ring in the fuel coupling attached 

to the wing front spar. We are issuing this AD 

to prevent fire and smoke at the engine aft 

pylon area in the event of a fuel leak, which 

could cause personal injury during ground 

operations. A fire spreading back and up to 

the aft fairing pylon can result in an 

uncontrolled fire in the strut and ignite the 

fuel tank. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Sealant Application 

Within 1,875 days after the effective date 

of this AD, apply sealant to fill the gap 

between the lower wing panels adjacent to 

the strut aft vapor barrier, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–54– 

0035, dated October 30, 2014. 

(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) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (h)(3)(i) and (h)(3)(ii) 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. 

(4) An AMOC that provides an acceptable 

level of safety may be used for any repair 

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. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(i) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6501; fax: 425–917–6590; 

email: kevin.nguyen@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 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. 

Issued in Renton, Washington, on June 30, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–16766 Filed 7–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2460; Directorate 

Identifier 2014–NM–163–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) 2010–26– 

10, which applies to certain The Boeing 

Company Model 747–200C, –200F, 

–400, –400D, and –400F series 

airplanes. AD 2010–26–10 currently 

requires repetitive inspections for 

cracking of the lap joints, modification 

of certain lap joints, and certain postrepair inspections of the lap joints. 

Since we issued AD 2010–26–10, an 

evaluation by the design approval 

holder (DAH) has indicated that certain 

lap joints are subject to widespread 

fatigue damage (WFD). This proposed 

AD would add new repetitive postmodification inspections for cracking in 

the lap joints, and repair if necessary. 

We are proposing this AD to detect and 

correct fatigue cracking in certain lap 

joints, which could result in rapid 

depressurization and consequent 

reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by August 24, 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– 

2460. 

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– 

2460; 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 


srobinson on DSK5SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 131 / Thursday, July 9, 2015 / Proposed Rules 39395 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@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–2015–2460; Directorate Identifier 

2014–NM–163–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 

On December 13, 2010, we issued AD 

2010–26–10, Amendment 39–16549 (75 

FR 81427, December 28, 2010), for 

certain Model 747–200C, –200F, –400, 

–400D, and –400F series airplanes. AD 

2010–26–10 requires repetitive 

inspections for cracking of the lap 

joints, modification of certain lap joints 

and certain post-repair inspections of 

the lap joints. AD 2010–26–10 resulted 

from a structural review of affected skin 

lap joints for WFD. We issued AD 2010– 

26–10 to prevent fatigue cracking in 

certain lap joints, which could result in 

rapid depressurization and consequent 

reduced structural integrity of the 

airplane. 

Widespread Fatigue Damage 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as widespread fatigue 

damage (WFD). As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

Actions Since AD 2010–26–10, 

Amendment 39–16549 (75 FR 81427, 

December 28, 2010), Was Issued 

Since we issued AD 2010–26–10, 

Amendment 39–16549 (75 FR 81427, 

December 28, 2010), an evaluation by 

the DAH has indicated that certain lap 

joints are subject to WFD. 

Related Service Information Under 1 

CFR part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014. The service 

information describes procedures for 

body skin lap joint inspections and 

modifications in sections 41, 42, and 43. 

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. 

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 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2010–26–10, Amendment 39–16549 (75 

FR 81427, December 28, 2010), this 

proposed AD would retain all of the 

requirements of AD 2010–26–10. Those 

requirements are referenced in the 

service information identified 

previously, which, in turn, is referenced 

in paragraphs (g) and (h) of this 

proposed AD. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Difference Between 

this Proposed AD and the Service 

Bulletin.’’ Refer to this service 

information for details on the 

procedures and compliance times. 

Difference Between This Proposed AD 

and the Service Bulletin 

Although Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014, specifies that 

operators may contact the manufacturer 

for disposition of certain repair 

conditions, this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 


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39396 Federal Register / Vol. 80, No. 131 / Thursday, July 9, 2015 / Proposed Rules 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Explanation of Compliance Time 

The compliance time for the 

modification specified in this proposed 

AD for addressing WFD was established 

to ensure that discrepant structure is 

modified before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. We will not grant any extensions 

of the compliance time to complete any 

AD-mandated service bulletin related to 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 120 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 

Pre–modification inspections 

[retained action from AD 

2010–26–10, Amendment 

39–16549 (75 FR 81427, 

December 28, 2010)].

Up to 675 work-hours, = up to 

$57,375.

$0 Up to $57,375 per inspection 

cycle.

Up to $6,885,000 per inspection cycle. 

Modification [retained action 

from AD 2010–26–10, 

Amendment 39–16549 (75 

FR 81427, December 28, 

2010)].

Up to 5,819 work-hours × $85 

per hour = up to $494,615.

0 Up to $494,615 ...................... Up to $59,353,800. 

New proposed post-modification inspections.Up to 105 work-hours × $85 

per hour = up to $8,925.

0 Up to $8,925 per inspection 

cycle.

Up to $1,071,000 per inspection cycle. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed AD. 

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 have 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 that the 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: 

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) 

2010–26–10, Amendment 39–16549 (75 

FR 81427, December 28, 2010), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2015–2460; Directorate Identifier 2014– 

NM–163–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 24, 2015. 

(b) Affected ADs 

This AD replaces AD 2010–26–10, 

Amendment 39–16549 (75 FR 81427, 

December 28, 2010). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–200C, –200F, –400, –400D, and 

–400F series airplanes; certificated in any 

category; as identified in Boeing Alert 

Service Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that certain lap joints are subject to 

widespread fatigue damage (WFD). We are 

issuing this AD to detect and correct fatigue 

cracking in certain lap joints, which could 

result in rapid depressurization and 

consequent reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Lap Joint Inspections 

At the applicable time specified in Table 

1 and Table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014, except as required by paragraph 

(j)(1) of this AD: Do eddy current inspections 

for cracks in the skin of the lap joints, and 

do all applicable repairs, in accordance with 

the Accomplishment Instructions of Boeing 


srobinson on DSK5SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 131 / Thursday, July 9, 2015 / Proposed Rules 39397 

Alert Service Bulletin 747–53A2499, 

Revision 3, dated July 15, 2014, except as 

required by paragraph (j)(2) of this AD. Do all 

applicable repairs before further flight. 

Repeat the applicable inspections thereafter 

at intervals not to exceed those specified in 

Table 1 and Table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014 

(h) Lap Joint Modification 

At the applicable time specified in Tables 

2, 4, 5, and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014, except as required by paragraph 

(j)(1) of this AD: Modify the applicable lap 

joints, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014, except as required by 

paragraph (j)(2) of this AD. Accomplishment 

of the modification required by this 

paragraph terminates the repetitive 

inspections required by paragraph (g) of this 

AD for the length of the modified lap joint. 

(i) Lap Joint Post-Modification Inspections 

At the applicable time specified in Tables 

7, 8, 9, and 10 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014, except as required by paragraph 

(j)(1) of this AD: Do the applicable 

inspections specified in paragraph (i)(1), 

(i)(2), or (i)(3) of this AD, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2499, 

Revision 3, dated July 15, 2014. Repeat the 

applicable inspections thereafter at the 

applicable times specified in Tables 7, 8, 9, 

and 10 of paragraph 1.E, ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2499, 

Revision 3, dated July 15, 2014. If any crack 

is found during any inspection, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(1) For airplanes identified as Groups 2 

through 5 and 8 through 10 in Boeing Alert 

Service Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014: Internal detailed and 

surface high frequency eddy current (HFEC) 

inspections for any crack in the skin or 

internal doubler. 

(2) For airplanes identified as Groups 6, 11, 

and 19 in Boeing Alert Service Bulletin 747– 

53A2499, Revision 3, dated July 15, 2014: 

External detailed and low frequency eddy 

current inspections of the upper and lower 

skin panels for cracking, external detailed 

and HFEC inspections of the doubler for 

cracking, and internal detailed and HFEC 

inspections of the upper and lower skin 

panels for cracking (for airplanes with a 

stringer 6 lap joint modification installed 

between STA 340 and STA 400 as specified 

in Boeing Service Bulletin 747–53–2272); or 

internal detailed and surface HFEC 

inspections for any crack in the skin or 

internal doubler (for airplanes with lap joints 

modified as specified in Boeing Alert Service 

Bulletin 747–53A2499.) 

(3) For airplanes identified as Groups 1, 7, 

and 12 through 18 in Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014: Internal detailed and surface HFEC 

inspections for any crack in the skin or 

internal doubler. 

(j) Exceptions to Service Bulletin Procedures 

(1) Where Boeing Alert Service Bulletin 

747–53A2499, Revision 3, dated July 15, 

2014, specifies a compliance time ‘‘after the 

Revision 3 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2499, Revision 3, dated July 15, 

2014, specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(k) Credit for Previous Actions 

Actions done before the effective date of 

this AD using the service information 

identified in paragraph (k)(1) or (k)(2) of this 

AD are acceptable for compliance with the 

corresponding requirements of paragraphs (g) 

and (h) of this AD. 

(1) Boeing Alert Service Bulletin 747– 

53A2499, Revision 1, dated October 30, 2008, 

which is not incorporated by reference in this 

AD. 

(2) Boeing Alert Service Bulletin 747– 

53A2499, Revision 2, dated August 12, 2010, 

which was incorporated by reference in AD 

2010–26–10, Amendment 39–16549 (75 FR 

81427, December 28, 2010). 

(l) 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 (m)(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 

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. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2010–26–10, 

Amendment 39–16549 (75 FR 81427, 

December 28, 2010), are approved as AMOCs 

for the corresponding provisions of 

paragraphs (g) and (h) this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@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 this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

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

Issued in Renton, Washington, on June 29, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–16763 Filed 7–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Parts 1, 301, and 602 

[REG–103281–11] 

RIN 1545–BK06 

Tax on Certain Foreign Procurement; 

Correction 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Correction to notice of proposed 

rulemaking. 

SUMMARY: This document contains 

corrections to a notice of proposed 

rulemaking (REG–103281–11) that was 

published in the Federal Register on 

Wednesday, April 22, 2015 (80 FR 

22449), the proposed regulations are 

relating to the 2 percent tax on 

payments made by the U.S. government 

to foreign persons pursuant to certain 

contracts. 

DATES: Written or electronic comments 

and request for a public hearing for the 

notice of proposed rulemaking at 80 FR 

22449, April 22, 2015, are still being 

accepted and must be received by July 

21, 2015. 

FOR FURTHER INFORMATION CONTACT: Kate 

Hwa, at (202) 317–6934 (not a toll-free 

number). 

SUPPLEMENTARY INFORMATION: 

Background 

The notice of proposed rulemaking 

that is the subject of this document is 

under section 5000C of the Internal 

Revenue Code. 


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