This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

38608 

Vol. 78, No. 124 

Thursday, June 27, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0538; Directorate 

Identifier 2012–NM–212–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This proposed AD was 

prompted by a report of cracks in 

stringer splices at body station STA 360 

and STA 908, between stringer (S) S– 

10L and S–10R; cracks in butt straps 

between S–5L and S–3L, and S–3R and 

S–5R; vertical chem-mill fuselage skin 

cracks at certain butt joints; and an 

instance of cracking that occurred in all 

those three structural elements on one 

airplane. This proposed AD would 

require repetitive inspections for any 

cracking of stringer splices and butt 

straps, and related corrective and 

investigative actions if necessary. We 

are proposing this AD to detect and 

correct cracking in the three structural 

elements, which could result in the 

airplane not being able to sustain limit 

load requirements and possibly result in 

uncontrolled decompression. 

DATES: We must receive comments on 

this proposed AD by August 12, 2013. 

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 

review copies of the 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0538; Directorate Identifier 2012– 

NM–212–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We received reports of 197 stringer 

splice cracks at body station (STA) 360 

and STA 908, between stringer (S) S– 

10L and S–10R; 16 butt strap cracks 

between S–5L and S–3L, and S–3R and 

S–5R; and 12 vertical chem-mill 

fuselage skin cracks at certain butt 

joints. On one airplane, a maintenance 

inspection found that all three structural 

elements were cracked. Analysis 

indicates the cracking of the stringer 

splices is attributed to airplane fatigue 

loads. Cracking of the butt strap at STA 

360 and STA 908 is attributed to fatigue 

loading from the S–4 lap joint. This 

condition, if not corrected, could result 

in the airplane not being able to sustain 

limit load requirements and possibly 

result in uncontrolled decompression. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–53A1322, dated November 

5, 2012. For information on the 

procedures and compliance times, see 

this service information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0538. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

The phrase ‘‘related investigative 

actions’’ might be used in this proposed 

AD. ‘‘Related investigative actions’’ are 

follow-on actions that: (1) Are related to 

the primary actions, and (2) are actions 

that further investigate the nature of any 

condition found. Related investigative 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Proposed Rules 38609 

actions in an AD could include, for 

example, inspections. 

In addition, the phrase ‘‘corrective 

actions’’ might be used in this proposed 

AD. ‘‘Corrective actions’’ are actions 

that correct or address any condition 

found. Corrective actions in an AD 

could include, for example, repairs. 

Differences Between the Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 737– 

53A1322, dated November 5, 2012, 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but 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 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Boeing Alert Service Bulletin 737– 

53A1322, dated November 5, 2012, 

specifies to contact the manufacturer for 

instructions on how to inspect airplanes 

having line number 1 through 291, but 

this proposed AD would require 

inspections in accordance with a 

method we approve. 

Costs of Compliance 

We estimate that this proposed AD 

affects 612 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 

Inspections ................................................................ Up to 362 work-hours × 

$85 per hour = 

$30,770, per inspection cycle.

None Up to $30,770, per inspection cycle.Up to $18,831,240, per 

inspection cycle 

Removal and reinstallation of butt strap fastener(s) Up to 2 work-hours × 

$85 per hour = $170, 

per inspection cycle.

$0 Up to $170, per inspection cycle.Up to $104,040, per inspection cycle 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Stringer splice replacement ........................................................... 3 work-hours × $85 per hour 

= $255.

Operator-supplied, information 

not available.

$255 

The work-hour estimate and parts cost 

information are not available for 

estimating the cost of a butt strap 

replacement. 

Authority for this Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2013–0538; Directorate Identifier 2012–NM– 

212–AD. 

(a) Comments Due Date 

We must receive comments by August 12, 

2013. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
38610 Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 / Proposed Rules 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

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

and –500 series airplanes, certified in any 

category, as identified in Boeing Alert 

Service Bulletin 737–53A1322, dated 

November 5, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracks in stringer splices at body station STA 

360 and STA 908, between stringer (S) S–10L 

and S–10R; cracks in butt straps between S– 

5L and S–3L, and S–3R and S–5R; vertical 

chem-mill fuselage skin cracks at certain butt 

joints; and an instance of cracking that 

occurred in all those three structural 

elements on one airplane. We are issuing this 

AD to detect and correct cracking in the three 

structural elements, which could result in the 

airplane not being able to sustain limit load 

requirements and possibly result in 

uncontrolled decompression. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Actions for Group 1 Airplanes 

For Group 1 airplanes, as identified in 

Boeing Alert Service Bulletin 737–53A1322, 

dated November 5, 2012: At the compliance 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1322, dated November 5, 

2012, except as provided by paragraph (j)(2) 

of this AD, inspect the stringers and butt 

straps and repair as applicable, using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(h) Actions for Groups 2 Through 6 

Airplanes 

For Groups 2 through 6 airplanes, as 

identified in Boeing Alert Service Bulletin 

737–53A1322, dated November 5, 2012: At 

the applicable compliance time specified in 

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

Alert Service Bulletin 737–53A1322, dated 

November 5, 2012, do the applicable 

inspections for cracking identified in 

paragraphs (h)(1) through (h)(4) of this AD, 

and all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1322, dated November 5, 2012, 

except as provided by paragraph (j) of this 

AD. Do all applicable corrective actions 

before further flight. Thereafter, repeat the 

applicable inspections at the compliance 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1322, dated November 5, 

2012. Accomplishing the corrective actions 

for a cracked stringer splice, as specified in 

Boeing Alert Service Bulletin 737–53A1322, 

dated November 5, 2012, terminates the 

repetitive inspections required by this 

paragraph for that stringer splice only. 

(1) Internal detailed inspections of the 

stringer splices and butt straps. 

(2) Internal high-frequency eddy current 

(HFEC) surface inspections of the butt straps. 

(3) Internal low-frequency eddy current 

(LFEC) inspection of the butt straps. 

(4) HFEC open hole rotary probe 

inspections of butt straps or of one location 

of a butt strap, as applicable. 

(i) Post-Repair Inspections 

The post-repair inspection specified in 

Table 11 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1322, 

dated November 5, 2012, is not required by 

this AD. 

Note 1 to paragraph (i) of this AD: The 

post-repair inspections specified in Table 11 

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

Alert Service Bulletin 737–53A1322, dated 

November 5, 2012, may be used in support 

of compliance with section 121.1109(c)(2) or 

129.109(b)(2) of the Federal Aviation 

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

129.109(b)(2)). The corresponding actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1322, dated November 5, 2012, are 

not required by this AD. 

(j) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

737–53A1322, dated November 5, 2012, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(2) Where Boeing Alert Service Bulletin 

737–53A1322, dated November 5, 2012, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(k) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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. 

(l) 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 

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 review copies of the 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 13, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–15425 Filed 6–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

SOCIAL SECURITY ADMINISTRATION 

[Docket No. 2011–0056] 

20 CFR Parts 404, 405, and 416 

RIN 0960–AH37 

Changes to Scheduling and Appearing 

at Hearings 

AGENCY: Social Security Administration. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: We propose to revise our 

rules to protect the integrity of our 

programs and preserve limited 

resources. Prior to scheduling a hearing, 

we will notify the claimant that his or 

her hearing may be held by video 

teleconferencing. The claimant will 

have an opportunity to object to 

appearing by video teleconferencing 

within 30 days after the date he or she 

receives the notice. We also propose 

changes that allow us to determine that 

a claimant will appear via video 

teleconferencing if he or she changes 

residences while his or her request for 

hearing is pending, regardless of 

whether or not the claimant previously 

declined a hearing by video 

teleconferencing. 

Additionally, we propose changes 

that require a claimant to notify us, in 

writing, of an objection to the time and 

place of hearing at the earliest 

opportunity, but not later than 5 days 

before the date set for the hearing, or, if 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS