15658 Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Proposed Rules 

that have a serial number with a suffix ‘B,’ 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–60, dated July 12, 2012. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an RFTU P/N 399500– 

1007 with a serial number from (S/N) 0008 

through 0509 inclusive, including serial 

numbers with suffix ‘A,’ on any airplane, 

except RFTUs that have a serial number with 

suffix ‘B,’ may be installed. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. 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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(k) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2012–02R1, dated October 12, 

2012; and Bombardier Service Bulletin 84– 

27–60, dated July 12, 2012; for related 

information. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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 February 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05597 Filed 3–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0206; Directorate 

Identifier 2012–NM–068–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 all The 

Boeing Company Model 727 airplanes. 

This proposed AD was prompted by 

reports of spanwise cracks and 

corrosion in the wing center box upper 

skin and rear spar upper chord between 

left buttock line (LBL) 70.50 and right 

buttock line (RBL) 70.50 at body station 

(STA) 870. This proposed AD would 

require repetitive inspections of the 

wing center box for cracking around 

certain fastener rows on the rear spar 

upper chord horizontal flange; for 

certain airplanes, repetitive inspections 

for cracking of the rear spar upper chord 

radius; for certain other airplanes, 

repetitive inspections for damage, 

cracking, and corrosion of the pressure 

seal; and repair if necessary. We are 

proposing this AD to detect and correct 

cracking and corrosion of the upper skin 

and rear spar upper chord of the wing 

center box, which could result in loss of 

the airplane wing and consequent loss 

of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 26, 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 Ave 

SW., Renton, WA. 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6577; 

fax: (425) 917–6590; email: 

berhane.alazar@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– 

2013–0206; Directorate Identifier 2012– 

NM–068–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received reports of spanwise 

cracks and corrosion in the wing center 

box upper skin and rear spar upper 

chord between LBL 70.50 and RBL 

70.50 at STA 870. The crack sizes 

ranged from 0.125 inches to 12 inches. 

The airplanes had accumulated between 

31,679 and 61,359 total flight hours and 

between 17,754 and 58,796 total flight 


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Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Proposed Rules 15659 

cycles. Analysis has shown that the 

cracks are a result of stress corrosion. 

This condition, if not detected and 

corrected, could result in loss of the 

airplane wing and consequent loss of 

control of the airplane. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 727–57– 

0187, dated March 8, 2012. For 

information on the procedures and 

compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0206. 

Related Rulemaking 

AD 2005–05–19, Amendment 39– 

14008 (70 FR 12120, March 11, 2005; 

corrected March 17, 2005 (70 FR 

13074)), requires repetitive detailed 

inspections to detect cracking, 

corrosion, minor surface defects, and 

existing stop-drilled repairs of cracks in 

the upper and lower chords of the front 

and rear spars of the wing; and repair if 

necessary. Those required actions are 

for locations between buttock line 70.5 

and the wing tip (i.e., left and right 

wings). This proposed AD would 

require actions between the LBL 70.5 

and RBL 70.5 of the rear spar upper 

chord and upper skin at STA 870 (i.e., 

center wing). 

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 

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 Special Attention Service 

Bulletin 727–57–0187, dated March 8, 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 98 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 

Inspection ........ 67 work-hours × $85 per hour = $5,695 per 

inspection cycle.

$0 $5,695 per inspection cycle .... $558,110 per inspection cycle 

We have received no definitive data 

that would enable us to provide cost 

estimates 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 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– 

2013–0206; Directorate Identifier 2012– 

NM–068–AD. 

(a) Comments Due Date 

We must receive comments by April 26, 

2013. 


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15660 Federal Register / Vol. 78, No. 48 / Tuesday, March 12, 2013 / Proposed Rules 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 727, 727C, 727–100, 727– 

100C, 727–200, and 727–200F series 

airplanes, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

spanwise cracks and corrosion in the wing 

center box upper skin and rear spar upper 

chord between left buttock line (LBL) 70.50 

and right buttock line (RBL) 70.50 at body 

station (STA) 870. We are issuing this AD to 

detect and correct cracking and corrosion of 

the upper skin and rear spar upper chord of 

the wing center box, which could result in 

loss of the airplane wing and consequent loss 

of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Except as specified in paragraph (h) of this 

AD, at the applicable time specified in 

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

Special Attention Service Bulletin 727–57– 

0187, dated March 8, 2012: Inspect the wing 

center box between LBL 70.50 and RBL 

70.50, at STA 870, as specified in paragraphs 

(g)(1), (g)(2), (g)(3), (g)(4), and (g)(5) of this 

AD, as applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 727–57– 

0187, dated March 8, 2012. Repeat the 

inspections thereafter at the applicable times 

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

Boeing Special Attention Service Bulletin 

727–57–0187, dated March 8, 2012. If any 

crack, corrosion, or damage is found during 

any inspection required by this AD, before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

(1) Do a high frequency eddy current 

(HFEC) or detailed inspection for cracking 

around the forward fastener row in the rear 

spar upper chord horizontal flange. 

(2) Do a low frequency eddy current 

inspection for cracking around the aft 

fastener row in the rear spar upper chord 

horizontal flange. 

(3) Do a detailed or HFEC inspection for 

cracking in the rear spar upper chord radius. 

(4) Do a detailed or HFEC inspection for 

cracking in the upper skin around the 

forward fastener row common to the rear spar 

upper chord horizontal flange. 

(5) Do a detailed inspection for damage, 

cracking, and corrosion in the pressure seal. 

(h) Exception to the Service Information 

Boeing Special Attention Service Bulletin 

727–57–0187, dated March 8, 2012, specifies 

compliance times ‘‘after the original issue 

date of this service bulletin.’’ However, this 

AD requires compliance within the specified 

compliance times ‘‘after the effective date of 

this AD.’’ 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6577; fax: (425) 917–6590; 

email: berhane.alazar@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 Ave SW., Renton, WA. 

For information on the availability of this 

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

Issued in Renton, Washington, on February 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05598 Filed 3–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

CONSUMER PRODUCT SAFETY 

COMMISSION 

[CPSC Docket No. CPSC–2013–0010] 

16 CFR Part 1500 

Hazardous Substances and Articles; 

Supplemental Definition of ‘‘Strong 

Sensitizer’’ 

AGENCY: Consumer Product Safety 

Commission. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The U.S. Consumer Product 

Safety Commission (CPSC or 

Commission) proposes to update the 

supplemental definition of ‘‘strong 

sensitizer’’ under the Federal Hazardous 

Substances Act (FHSA). The proposed 

amendment clarifies or adds language to 

eliminate redundancy, remove certain 

subjective factors, incorporate new and 

anticipated technology, rank the criteria 

for classification of strong sensitizers in 

order of importance, define criteria for 

‘‘severity of reaction,’’ and indicate that 

a weight-of-evidence approach will be 

used to determine the strength of the 

sensitizer. 

DATES: Written comments must be 

received by May 28, 2013. 

ADDRESSES: You may submit comments 

identified by Docket No. CPSC–2013– 

0010, by any of the following methods: 

• Electronic Submissions 

Submit electronic comments in the 

following way: 

Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

To ensure timely processing of 

comments, the Commission is no longer 

accepting comments submitted by 

electronic mail (email) except through 

www.regulations.gov. 

• Written Submissions 

Submit written submissions in the 

following way: 

Mail/Hand delivery/Courier (for 

paper, disk, or CD–ROM submissions), 

preferably in five copies, to: Office of 

the Secretary, U.S. Consumer Product 

Safety Commission, Room 820, 4330 

East West Highway, Bethesda, MD 

20814; telephone (301) 504–7923. 

Instructions: All submissions received 

must include the agency name and 

docket number for this proposed 

rulemaking. All comments received may 

be posted without change, including 

any personal identifiers, contact 

information, or other personal 

information provided, to http:// 

www.regulations.gov. Do not submit 

confidential business information, trade 

secret information, or other sensitive or 

protected information electronically. 


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