Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Proposed Rules 61133 

72–A408, Circulation B, dated January 2015; 

ASB Mk. 522 Number 72–A413, Circulation 

A, dated January 2015; ASB Mk. 522 Number 

72–A412, Circulation B, dated January 2015; 

and ASB Mk. 601–22 Number 72–A207, 

dated January 2015, to determine the new life 

limits. 

(2) For the RR Viper Mk. 601–22 turbojet 

engine, remove compressor shaft, part 

number V900766, before the compressor 

shaft accumulates 20,720 flight cycles since 

new. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any affected part identified in 

paragraph (e) of this AD into any engine, nor 

return any engine to service with any affected 

part identified in paragraph (e) of this AD 

installed, if any affected part exceeds the life 

limit specified in the appropriate ASB 

identified in paragraph (e)(1) and/or the life 

limit identified in paragraph (e)(2) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

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 Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7770; fax: 781–238–7199; 

email: philip.haberlen@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0127R1, dated 

August 14, 2015, for more information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2012–1331. 

(3) RR ASB Mk. 521 Number 72–A408, 

Circulation A, dated January 2015; ASB Mk. 

521 Number 72–A408, Circulation B, dated 

January 2015; ASB Mk. 522 Number 72– 

A413, Circulation A, dated January 2015; 

ASB Mk. 522 Number 72–A412, Circulation 

B, dated January 2015; and ASB Mk. 601–22 

Number 72–A207, dated January 2015, can be 

obtained from RR, using the contact 

information in paragraph (h)(4) of this 

proposed AD. 

(4) For service information identified in 

this AD, contact DA Services Operations 

Room at Rolls-Royce plc, Defense Sector 

Bristol, WH–70, P.O. Box 3, Filton, Bristol 

BS34 7QE, United Kingdom; phone: +44 (0) 

117 97 90700; fax: +44 (0) 117 97 95498; 

email: defence-operations-room@rollsroyce.com. 

(5) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

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

Issued in Burlington, Massachusetts, on 

October 2, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–25607 Filed 10–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3984; Directorate 

Identifier 2015–NM–033–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) 2008–13– 

12 R1, which applies to certain The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. AD 2008–13–12 R1 currently 

requires various repetitive inspections 

for cracking of the upper frame to side 

frame splice of the fuselage, and other 

specified and corrective actions if 

necessary; and also provides for an 

optional preventive modification, which 

terminates the repetitive inspections. 

Since we issued AD 2008–13–12 R1, we 

have received reports of additional 

fatigue cracking of the upper frame to 

side frame splice of the fuselage, and 

two reports of severed frames. This 

proposed AD would add, for certain 

airplanes, an inspection to determine if 

the existing frame repair meets all 

specified requirements; for certain other 

airplanes, a new modification of the 

upper frame to side frame splice, which 

would terminate the repetitive 

inspections; and reduce certain 

inspection thresholds and repetitive 

intervals. We are proposing this AD to 

detect and correct fatigue cracking of the 

upper frame to side frame splice of the 

fuselage, which could result in reduced 

structural integrity of the frame and 

adjacent lap joint, causing increased 

loading in the fuselage skin, which will 

accelerate skin crack growth and result 

in decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 23, 

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– 

3984. 

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– 

3984; 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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6447; fax: 

425–917–6590; email: wayne.lockett@

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–2015–3984; Directorate Identifier 


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61134 Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Proposed Rules 

2015–NM–033–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 June 12, 2008, we issued AD 

2008–13–12, Amendment 39–15575 (73 

FR 38905, July 8, 2008), which was 

revised by AD 2008–13–12 R1, 

Amendment 39–15719 (73 FR 67383, 

November 14, 2008), for certain The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. AD 2008–13–12 R1 requires 

various repetitive inspections for 

cracking of the upper frame to side 

frame splice of the fuselage, and other 

specified and corrective actions if 

necessary. AD 2008–13–12 R1 also 

provides for an optional preventive 

modification, which terminates the 

repetitive inspections. AD 2008–13–12 

R1 resulted from a report that the upper 

frame of the fuselage was severed 

between stringers S–13L and S–14L at 

station 747, and the adjacent frame at 

station 767 had a 1.3-inch-long crack at 

the same stringer location. We issued 

AD 2008–13–12 R1 to detect and correct 

fatigue cracking of the upper frame to 

side frame splice of the fuselage, which 

could result in reduced structural 

integrity of the frame and adjacent lap 

joint. This reduced structural integrity 

can increase loading in the fuselage 

skin, which will accelerate skin crack 

growth and result in decompression of 

the airplane. 

Widespread Fatigue Damage (WFD) 

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 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 

design approval holder (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 2008–13–12 R1, 

Amendment 39–15719 (73 FR 67383, 

November 14, 2008) Was Issued 

Since AD 2008–13–12 R1, 

Amendment 39–15719 (73 FR 67383, 

November 14, 2008) was issued, we 

have received reports of additional 

fatigue cracking of the upper frame to 

side frame splice of the fuselage, and 

two reports of severed frames. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–53A1261, Revision 1, 

dated January 30, 2015. The service 

information describes procedures for 

various repetitive inspections for 

cracking of the upper frame to side 

frame splice of the fuselage, an 

inspection to determine if the existing 

frame repair meets all specified 

requirements, and corrective actions if 

necessary. The service information also 

describes procedures for a new 

preventive modification, which would 

eliminate the need for the repetitive 

inspections. 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 

2008–13–12, Amendment 39–15575 (73 

FR 38905, July 8, 2008), revised by AD 

2008–13–12 R1, Amendment 39–15719 

(73 FR 67383, November 14, 2008), this 

proposed AD would retain all of the 

requirements of those ADs. Those 

requirements are referenced in the 

service information identified 

previously, which, in turn, is referenced 

in paragraph (g) of this proposed AD. 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. Refer to this service 

information for information on the 

procedures and compliance times. 

Explanation of Proposed 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 


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Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Proposed Rules 61135 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 391 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 

Retained inspections 

from AD 2008–13–12, 

Amendment 39– 

15575 (73 FR 38905, 

July 8, 2008).

Between 18 and 38 work-hours × $85 per hour, 

depending on airplane configuration = between $1,530 and $3,230 per inspection 

cycle.

$0 Between $1,530 and 

$3,230 per inspection 

cycle.

Between $598,230 and 

$1,262,930 per inspection cycle. 

New inspections ............ 213 work-hours × $85 per hour, $18,105 per inspection cycle.0 $18,105 per inspection 

cycle.

$7,079,055 per inspection cycle. 

New modification ........... 256 work-hours × $85 per hour = $21,760 ........ ........................ $21,760 ........................ $8,508,160. 

We currently have no specific cost 

estimates associated with the parts 

necessary for the proposed 

modification. 

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) 

2008–13–12 R1, Amendment 39–15719 

(73 FR 67383, November 14, 2008), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2015–3984; Directorate Identifier 2015– 

NM–033–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by November 23, 2015. 

(b) Affected ADs 

This AD replaces AD 2008–13–12 R1, 

Amendment 39–15719 (73 FR 67383, 

November 14, 2008). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–100, –200, –200C, –300, –400, 

and –500 series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 737–53A1261, Revision 1, 

dated January 30, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking of the upper frame to side 

frame splice of the fuselage, and two reports 

of severed frames. We are issuing this AD to 

detect and correct fatigue cracking of the 

upper frame to side frame splice of the 

fuselage, which could result in reduced 

structural integrity of the frame and adjacent 

lap joint, causing increased loading in the 

fuselage skin, which will accelerate skin 

crack growth and result in decompression of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Corrective 

Actions for Certain Airplanes 

(1) For Groups 1 through 3, Configurations 

1, 3, 4, and 5 airplanes; Group 7, 

Configurations 1, 3, 4, and 5 airplanes; 

Groups 4 through 6, Configurations 1, 3, 4, 

and 6 airplanes; and Groups 8 through 11, 

Configurations 1, 3, 4, and 6 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Do the actions specified in paragraphs 

(g)(1)(i) and (g)(1)(ii) of this AD, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD. Do all 

applicable corrective actions before further 

flight. 

(i) At the applicable time specified in 

Tables 1, 2, 3, 5, 6, and 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1261, Revision 1, dated 

January 30, 2015, except as required by 

paragraphs (i)(1) and (i)(2) of this AD: Do 

medium frequency eddy current inspections 

for cracking of the upper frame to side frame 

splice of the fuselage. 

(ii) Repeat the inspections specified in 

paragraph (g)(1)(i) of this AD at the 

applicable time specified in Tables 1, 2, 3, 5, 

6, and 8 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015. 


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(2) For Groups 4 through 6, Configurations 

2 and 5 airplanes; and Groups 8 through 11, 

Configurations 2 and 5 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Do the actions specified in paragraphs 

(g)(2)(i) and (g)(2)(ii) of this AD, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD. Do all 

applicable corrective actions before further 

flight. 

(i) At the applicable time specified in 

Tables 4 and 7 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1261, Revision 1, dated 

January 30, 2015, except as required by 

paragraphs (i)(1) and (i)(2) of this AD: Do a 

detailed inspection to determine if the 

existing frame repair meets all requirements 

specified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015, and for any frame that does meet all 

requirements, do detailed and high frequency 

eddy current (HFEC) inspections for cracking 

of certain tied frames. 

(ii) Repeat the inspections for cracking 

specified in paragraph (g)(2)(i) of this AD at 

the applicable time specified in Tables 4 and 

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

Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015. 

(h) Post-Repair and Post-Modification 

Actions for Certain Airplanes 

For Group 1, Configurations 2 and 6 

airplanes; Group 2, Configurations 2 and 6 

airplanes; Group 3, Configurations 2 and 6 

airplanes; and Group 7, Configurations 2 and 

6 airplanes; as identified in Boeing Alert 

Service Bulletin 737–53A1261, Revision 1, 

dated January 30, 2015: Within 120 days after 

the effective date of this AD, do post-repair 

and post-modification actions using a 

method approved in accordance with the 

procedures specified in paragraph (n) of this 

AD. 

(i) Exceptions to Service Bulletin 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015, specifies a compliance time ‘‘after the 

Revision 1 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where the Condition column of 

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

Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, specifies 

a condition based on whether an airplane has 

or has not been inspected, this AD bases the 

condition on whether an airplane has or has 

not been inspected as of the effective date of 

this AD. 

(3) Where Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015, specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (n) of 

this AD. 

(j) Post-Repair/Post-Modification Inspections 

Not Required 

The post-repair/post-modification 

inspections specified in Tables 12 through 17 

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

Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, are not 

required by this AD, but may be used in 

support of compliance with section 

121.1109(c)(2) or 129.109(c)(2) of the Federal 

Aviation Regulations (14 CFR 121.1109(c)(2) 

or 14 CFR 129.109(c)(2)). 

(k) Preventative Modification for Certain 

Airplanes 

For Groups 4 through 6, Configurations 1, 

3, 4, and 6 airplanes; and Groups 8 through 

11, Configurations 1, 3, 4, and 6 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Except as provided by paragraphs (i)(1) 

and (i)(2) of this AD, at the applicable time 

specified in Tables 3, 5, 6, and 8 in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1261, Revision 1, dated 

January 30, 2015, do the preventive 

modification, including doing detailed and 

HFEC inspections for cracking and applicable 

corrective actions in accordance with Part 4 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD. Do all 

applicable corrective actions before further 

flight. Accomplishing the modification 

required by this paragraph terminates the 

inspections required by paragraph (g)(1) of 

this AD for the modified area only. 

(l) Terminating Action 

(1) For Groups 4 through 6, Configurations 

1, 3, 4, and 6 airplanes; and Groups 8 through 

11, Configurations 1, 3, 4, and 6 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Accomplishing the preventive 

modification, including detailed and HFEC 

inspections for cracking and applicable 

corrective actions, in accordance with Part 4 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD, 

terminates the inspections required by 

paragraph (g)(1) of this AD for the modified 

area only. 

(2) For Groups 4 through 6, Configurations 

3 and 6 airplanes; and Groups 8 through 11, 

Configurations 3 and 6 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Accomplishing the repair, including 

HFEC inspections for cracking and applicable 

corrective actions, in accordance with Part 3 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD, 

terminates the repetitive inspections required 

by paragraph (g)(1) of this AD for the repaired 

area only. 

(3) Accomplishment of the repair or the 

preventative modification specified in Boeing 

Message M–7200–02–1294, dated August 20, 

2002, before the effective date of this AD 

terminates the repetitive inspections required 

by paragraph (g)(1) of this AD for the repaired 

or modified area only. 

(4) Accomplishment of the repair or the 

preventative modification in accordance with 

a method approved by the Manager, Los 

Angeles Aircraft Certification Office (ACO) 

terminates the repetitive inspections required 

by paragraph (g)(1) of this AD for the repaired 

or modified area only. 

(m) Credit for Previous Actions 

(1) This paragraph provides credit for the 

inspections required by paragraph (g) of this 

AD, if those inspections were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 737–53A1261, 

dated January 19, 2006, which was 

incorporated by reference in AD 2008–13–12, 

Amendment 39–15575 (73 FR 38905, July 8, 

2008). 

(2) This paragraph provides credit for the 

modification specified in paragraphs (k) and 

(l)(1) of this AD, if performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 737–53A1261, dated January 

19, 2006, which was incorporated by 

reference in AD 2008–13–12, Amendment 

39–15575 (73 FR 38905, July 8, 2008). 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (o)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-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, Los Angeles 

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 2008–13–12, 

Amendment 39–15575 (73 FR 38905, July 8, 

2008); and AD 2008–13–12 R1, Amendment 

39–15719 (73 FR 67383, November 14, 2008); 

are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6447; fax: 425–917–6590; 

email: wayne.lockett@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 


rmajette on DSK7SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Proposed Rules 61137 

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 

September 29, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–25709 Filed 10–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Part 774 

[Docket No. 150820757–5757–01] 

Commerce Control List: Request for 

Comments Regarding Controls on 

Military Vehicles, Vessels of War, 

Submersible Vessels, Oceanographic 

Equipment, and Auxiliary and 

Miscellaneous Military Equipment 

AGENCY: Bureau of Industry and 

Security, Commerce. 

ACTION: Notice of inquiry. 

SUMMARY: The Bureau of Industry and 

Security (BIS), Department of 

Commerce, maintains the Export 

Administration Regulations, including 

the Commerce Control List (CCL). The 

Export Control Reform Initiative, a 

fundamental reform of the U.S. export 

control system, has resulted in transfer 

to the CCL of items that the President 

has determined do not warrant control 

on the United States Munitions List 

(USML), including certain military 

vehicles, vessels of war, submersible 

vessels, oceanographic equipment, 

auxiliary and miscellaneous military 

equipment, and related items therefor. 

The USML is part of the International 

Traffic in Arms Regulations maintained 

by the Department of State. Through 

this notice, BIS is seeking public 

comments to perform a complementary 

review of the aforementioned items on 

the CCL, concurrent with the 

Department of State’s review of the 

controls implemented in its recent 

revisions to Categories VI, VII, XIII, and 

XX of the USML (which control surface 

vessels of war and special naval 

equipment, military ground vehicles, 

miscellaneous military articles and 

materials, submersible vessels, and 

related items therefor), to ensure that 

the descriptions of these items on the 

CCL are clear, do not inadvertently 

control items in normal commercial use, 

account for technological developments, 

and properly implement the national 

security and foreign policy objectives of 

the reform effort. This notice also 

furthers the retrospective regulatory 

review directed by the President in 

Executive Order 13563. 

DATES: Comments must be received by 

BIS no later than December 8, 2015. 

ADDRESSES: Comments may be 

submitted to the Federal rulemaking 

portal (http://www.regulations.gov). You 

can find this notice by searching on its 

regulations.gov docket number, which is 

BIS–2015–0039. Comments may also be 

submitted via email to 

publiccommments@bis.doc.gov or on 

paper to Regulatory Policy Division, 

Bureau of Industry and Security, Room 

2099B, U.S. Department of Commerce, 

Washington, DC 20230. Please refer to 

RIN 0694–XC025 in all comments and 

in the subject line of email comments. 

All comments (including any personally 

identifying information) will be made 

available for public inspection and 

copying. Commerce’s full plan for 

retrospective regulatory review can be 

accessed at: http://open.commerce.gov/

news/2011/08/23/commerce-planretrospective-analysis-existing-rules. 

FOR FURTHER INFORMATION CONTACT: For 

questions regarding ground vehicles and 

related items (ECCNs 0A606, 0B606, 

0C606, 0D606 and 0E606), contact Gene 

Christiansen, Office of National Security 

and Technology Transfer Controls, at 

202–482–2984 or gene.christiansen@

bis.doc.gov. For questions regarding 

surface vessels and related items 

(ECCNs 8A609, 8B609, 8C609, 8D609 

and 8E609) or submersible vessels and 

related items (ECCNs 8A620, 8B620, 

8D620, and 8E620), contact Alexander 

Lopes, Office of Nonproliferation and 

Treaty Compliance, at 202–482–4875 or 

alexander.lopes@bis.doc.gov. For 

questions regarding miscellaneous 

equipment, materials, and related items 

(ECCNs 0A617, 0B617, 0C617, 0D617, 

and 0E617), contact Michael Rithmire, 

Office of National Security and 

Technology Transfer Controls, at 202– 

482–6105 or michael.rithmire@

bis.doc.gov. For questions regarding 

license applications for any of the items 

specified above, contact Elena Love, 

Thomas DeFee or Jeffery Leitz of the 

Office of Strategic Industries and 

Economic Security, by phone, at 202– 

482–4506, or by email, at Elena.Love@

bis.doc.gov, Thomas.DeFee@bis.doc.gov, 

or Jeffrey.Leitz@bis.doc.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The Bureau of Industry and Security 

(BIS), Department of Commerce 

maintains the Export Administration 

Regulations, including the Commerce 

Control List (CCL). The Export Control 

Reform Initiative, a fundamental reform 

of the U.S. export control system, has 

resulted in transfer to the CCL of items 

that the President has determined do 

not warrant control on the United States 

Munitions List (USML), including 

certain military vehicles, vessels of war, 

submersible vessels, oceanographic 

equipment, auxiliary and miscellaneous 

military equipment, and related items 

therefor. The USML is part of the 

International Traffic in Arms 

Regulations maintained by the 

Department of State. Through this 

notice, BIS is seeking comments to 

perform a complementary review of 

military vehicles, vessels of war, 

submersible vessels, oceanographic 

equipment, auxiliary and miscellaneous 

military equipment, and related items 

on the CCL, concurrent with the 

Department of State’s review of the 

controls implemented in its recent 

revisions to Categories VI, VII, XIII, and 

XX of the USML (which control surface 

vessels of war and special naval 

equipment, military ground vehicles, 

miscellaneous military articles and 

materials, submersible vessels, and 

related items therefor), to ensure that 

the descriptions of these items on the 

CCL are clear, do not inadvertently 

control items in normal commercial use, 

account for technological developments, 

and properly implement the national 

security and foreign policy objectives of 

the reform effort. 

Specifically, BIS is soliciting 

comments on the clarity, usability and 

any other matters related to 

implementation of the ‘‘600 series’’ 

Export Control Classification Numbers 

(ECCNs) that control the following 

items, as well as certain items related 

thereto: military vehicles (ECCNs 

0A606, 0B606, 0C606, 0D606, and 

0E606); vessels of war (ECCNs 8A609, 

8B609, 8C609, 8D609, and 8E609); 

submersible vessels and oceanographic 

equipment (ECCNs 8A620, 8B620, 

8D620, and 8E620); and auxiliary and 

miscellaneous military equipment 

(ECCNs 0A617, 0B617, 0C617, 0D617, 

and 0E617). 

The Export Control Reform Initiative: 

USML Review and the CCL 

A core element of the Export Control 

Reform (ECR) Initiative has been the 

streamlining of categories on the USML 

and the control on the CCL of those 

items that the President determines do 


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