71296 Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 

SMALL BUSINESS ADMINISTRATION 

13 CFR Part 121 

RIN 3245–AG47 

Small Business Size Standards; 

Adoption of 2012 North American 

Industry Classification System for Size 

Standards; Correction 

AGENCY: U.S. Small Business 

Administration. 

ACTION: Interim final rule; correction. 

SUMMARY: The U.S. Small Business 

Administration (SBA) is correcting an 

interim final rule that appeared in the 

Federal Register on August 20, 2012 (75 

FR 49991), effective October 1, 2012. 

The interim rule amended SBA’s Small 

Business Size Regulations by 

incorporating the Office of Management 

and Budget’s 2012 North American 

Industry Classification System update 

(NAICS 2012) into its table of small 

business size standards. The NAICS 

2012 revised the definitions of some 

NAICS industries by deleting some and 

merging others with the new or other 

revised industries. This action corrects 

the small business size standard for 

NAICS 334419, Other Electronic 

Component Manufacturing, from 500 

employees to 750 employees, effective 

immediately. 

DATES: Effective December 2, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Khem Sharma, Chief, Office of Size 

Standards, U.S. Small Business 

Administration, 409 Third Street SW., 

Washington, DC 20416. 

SUPPLEMENTARY INFORMATION: The 

NAICS 2012 revised the NAICS 2007 

definition for NAICS 334419, Other 

Electronic Component Manufacturing, 

by merging with it NAICS 334411, 

Electron Tube Manufacturing, but 

retained the existing industry title. 

NAICS 334419 had a size standard of 

500 employees, while NAICS 334411 

had 750 employees. In accordance with 

SBA’s policy of adopting the highest 

size standard among the industries 

merged, on page 50001 of the August 20, 

2012 interim final rule (75 FR 49991), 

SBA indicated in Table 2 ‘‘NAICS 2012 

Codes Matched to NAICS 2007 Codes 

and Size Standards’’ that it is adopting 

750 employees as the small business 

size standard for the revised NAICS 

334419. To amend the table in 

§ 121.201, ‘‘Small Business Size 

Standards by NAICS Industry’’, on page 

50008, the rule states ‘‘ttt. Remove the 

entries for 334411, 334414, and 

334415’’. However, the rule did not 

revise the size standard for NAICS 

344119 to 750 employees. Therefore, the 

revised table, ‘‘Small Business Size 

Standards by NAICS Industry’’ shows 

the old, incorrect size standard of 500 

employees for NAICS 334419. 

Need For Correction 

The purpose of this action is to 

correct the table ‘‘Small Business Size 

Standards by NAICS Industry’’ (13 CFR 

121.201) by revising the size standard 

for NAICS 334419, Other Electronic 

Component Manufacturing, from 500 

employees to 750 employees. 

List of Subjects in 13 CFR Part 121 

Administrative practice and 

procedure, Government procurement, 

Government property, Grant programs— 

business, Individuals with disabilities, 

Loan programs—business, Reporting 

and recordkeeping requirements, Small 

businesses. 

For the reasons set forth in the 

preamble, SBA amends 13 CFR part 121 

by making the following correcting 

amendment: 

PART 121—SMALL BUSINESS SIZE 

REGULATIONS 

■ 1. The authority citation for part 121 

continues to read as follows: 

Authority: 15 U.S.C. 632, 634(b)(6), 636(b), 

662, 694a(9). 

■ 2. In § 121.201, revise the entry 

‘‘334419’’ in the table, ‘‘Small Business 

Size Standards by NAICS Industry’’ to 

read as follows: 

§ 121.201 What size standards has SBA 

identified by North American Industry 

Classification System codes? 

* * * * * 

SMALL BUSINESS SIZE STANDARDS BY NAICS INDUSTRY

NAICS 

codes NAICS U.S. industry title 

Size standards 

in millions of 

dollars 

Size standards 

in number of 

employees 

*******

334419 ............................................. Other Electronic Component Manufacturing ............................................. ........................ 750 

* * * * * * * 

Dated: November 18, 2014. 

Kenneth Dodds, 

Director for Office of Policy, Planning and 

Liaison. 

[FR Doc. 2014–28329 Filed 12–1–14; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0195; Directorate 

Identifier 2013–NM–195–AD; Amendment 

39–18026; AD 2014–23–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–17– 

03 for certain The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. AD 

2008–17–03 required repetitive 

inspections to detect fuselage frame 

cracking, and corrective action if 

necessary. AD 2008–17–03 also 

provided for optional terminating action 

(repair/preventive change) for the 

repetitive inspections. This new AD 

adds airplanes to the applicability, but 

does not provide terminating action for 

the newly added airplanes. This AD was 

prompted by reports of cracks found at 

the cutout in the web of body station 

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Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 71297 

frame 303.9 inboard of stringer 16L, as 

well as a new report of cracking found 

on an airplane not identified in the 

applicability of AD 2008–17–03. We are 

issuing this AD to detect and correct 

fuselage frame cracking, which could 

prevent the left forward entry door from 

sealing correctly, and could cause inflight decompression of the airplane. 

DATES: This AD is effective January 6, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of September 23, 2008 (73 FR 

48288, August 19, 2008). 

ADDRESSES: 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. 

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–2014– 

0195; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nenita Odessa, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: 562–627–5234; fax: 562–627– 

5210; email: nenita.odessa@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, 

August 19, 2008). AD 2008–17–03 

applied to certain The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. The 

NPRM published in the Federal 

Register on April 14, 2014 (79 FR 

20824). The NPRM was prompted by 

reports of cracks found at the cutout in 

the web of body station frame 303.9 

inboard of stringer 16L, and the 

subsequent determination that 

additional airplanes are subject to the 

requirements of AD 2008–17–03. The 

NPRM proposed to continue to require 

repetitive inspections for fuselage frame 

cracking and applicable corrective 

action, add airplanes to the 

applicability, and to provide optional 

terminating action (repair/preventive 

change) for the repetitive inspections for 

the airplanes subject to AD 2008–17–03. 

We are issuing this AD to detect and 

correct fuselage frame cracking, which 

could prevent the left forward entry 

door from sealing correctly, and could 

cause in-flight decompression of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 20824, 

April 14, 2014) and the FAA’s response 

to each comment. 

Effect of Winglets on This AD 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/

$FILE/ST01219SE.pdf) does not affect 

the actions specified in the NPRM (79 

FR 20824, April 14, 2014). 

We concur with the commenter. We 

have redesignated paragraphs (c), (c)(1), 

and (c)(2) of the NPRM (79 FR 20824, 

April 14, 2014) as paragraphs (c)(1), 

(c)(1)(i), and (c)(1)(ii) of this AD, and 

added new paragraph (c)(2) to this AD 

to state that installation of STC 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/

$FILE/ST01219SE.pdf) does not affect 

the ability to accomplish the actions 

required by this AD. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. 

Request To Clarify Certain 

Requirements 

All Nippon Airways (ANA) requested 

that we revise paragraph (i) of the 

proposed AD (79 FR 20824, April 14, 

2014), which added new inspections for 

Group 2 airplanes in accordance with 

Boeing Alert Service Bulletin 737– 

53A1188, Revision 3, dated September 

6, 2013. ANA claimed that this 

requirement included unnecessary 

procedures for opening and closing 

access from the aft side of the inspection 

area because the inspection is required 

from the forward side. ANA suggested 

that we include the information in Note 

8 of paragraph 3.A., General 

Instructions, of Boeing Alert Service 

Bulletin 737–53A1188, Revision 3, 

dated September 6, 2013, to exclude the 

unnecessary procedures. Note 8 states, 

in part, as follows: 

If it is necessary to remove more parts for 

access, you can remove those parts. If you 

can get access without removing identified 

parts, it is not necessary to remove all of the 

identified parts. . . . 

We agree with the request. We have 

revised paragraph (i) in this AD to point 

to this exception in new paragraph (j)(4) 

in this AD. We have similarly changed 

paragraphs (g) and (h) in this AD to also 

specify this exception. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (73 FR 

20824, April 14, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (73 FR 20824, 

April 14, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 148 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

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ESTIMATED COSTS: REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Inspection ...................... 31 to 33 work-hours × $85 per hour = up to 

$2,805 per inspection cycle.

$0 Up to $2,805 per inspection cycle.Up to $415,140 per inspection cycle 

ESTIMATED COSTS: OPTIONAL MODIFICATION

Action Labor cost Parts cost Cost per product 

Repair/preventive change ...................... 12 to 30 work-hours × $85 per hour = up to 

$2,550.

$564 to $2,236 .............. Up to $4,786 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this 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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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) 

2008–17–03, Amendment 39–15641 (73 

FR 48288, August 19, 2008), and adding 

the following new AD: 

2014–23–10 The Boeing Company: 

Amendment 39–18026; Docket No. 

FAA–2014–0195; Directorate Identifier 

2013–NM–195–AD. 

(a) Effective Date 

This AD is effective January 6, 2015. 

(b) Affected ADs 

This AD replaces AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, August 

19, 2008). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company airplanes, certificated in any 

category, identified in paragraphs (c)(1)(i) 

and (c)(1)(ii) of this AD. 

(i) Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes, as identified 

in Boeing Alert Service Bulletin 737– 

53A1197, dated August 25, 2006. 

(ii) Model 737–300, –400, and –500 series 

airplanes, as identified in Boeing Alert 

Service Bulletin 737–53A1188, Revision 3, 

dated September 6, 2013. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/$FILE/

ST01219SE.pdf) does not affect the ability to 

accomplish the actions required by this AD. 

For airplanes on which STC ST01219SE 

(http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/$FILE/

ST01219SE.pdf) is installed, therefore, a 

‘‘change in product’’ alternative method of 

compliance (AMOC) approval request is not 

necessary to comply with the requirements of 

14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found at the cutout in the web of body station 

frame 303.9 inboard of stringer 16L, and a 

new report of cracking found on an airplane 

not included in the applicability of AD 2008– 

17–03, Amendment 39–15641 (73 FR 48288, 

August 19, 2008). We are issuing this AD to 

detect and correct such cracking, which 

could prevent the left forward entry door 

from sealing correctly, and could cause inflight decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections: Group 1 

Airplanes, Boeing Alert Service Bulletin 

737–53A1188, Revision 2, Dated May 9, 

2007; or Boeing Alert Service Bulletin 737– 

53A1188, Revision 3, Dated September 6, 

2013 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–17–03, Amendment 

39–15641 (73 FR 48288, August 19, 2008), 

with revised service information and airplane 

groupings. For airplanes identified as Group 

1 in Boeing Alert Service Bulletin 737– 

53A1188, Revision 3, dated September 6, 

2013: Do detailed and high frequency eddy 

current (HFEC) inspections in the web and 

doubler around the slotted holes in the frame 

web at stringers 15L and 16L, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 2, dated May 9, 2007; or Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013, except 

as provided by paragraph (j)(4) of this AD. Do 

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Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 71299 

the inspections at the applicable time 

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

Boeing Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013. Do all 

applicable corrective actions before further 

flight in accordance with Boeing Alert 

Service Bulletin 737–53A1188, Revision 2, 

dated May 9, 2007; or Boeing Alert Service 

Bulletin 737–53A1188, Revision 3, dated 

September 6, 2013; except as provided by 

paragraph (j)(3) of this AD. Repeat the 

inspections at intervals not to exceed 4,500 

flight cycles, until accomplishment of the 

repair/preventive change in accordance with 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 2, dated May 9, 2007; or Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013; which 

terminates the repetitive inspection 

requirements for the airplanes identified in 

this paragraph. A repair/preventive change 

done using Boeing Alert Service Bulletin 

737–53A1188, dated April 9, 1998; or Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 1, dated March 18, 1999; does not 

terminate the repetitive inspections, but the 

repetitive inspections may be terminated 

after the existing kit is replaced with a new 

kit in accordance with paragraph 3.B., Part II, 

step 3, or Part III, step 3, of Boeing Alert 

Service Bulletin 737–53A1188, Revision 2, 

dated May 9, 2007. As of the effective date 

of this AD, only Boeing Alert Service Bulletin 

737–53A1188, Revision 3, dated September 

6, 2013, may be used to do the actions 

required by this paragraph. 

Note 1 to paragraph (g) of this AD: 

Airplanes identified as Group 1 in Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013, are the 

same as those identified in Boeing Alert 

Service Bulletin 737–53A1188, Revision 2, 

dated May 9, 2007. 

(h) Retained Repetitive Inspections: Boeing 

Alert Service Bulletin 737–53A1197, Dated 

August 25, 2006 

This paragraph restates the requirements of 

paragraph (g) of AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, August 

19, 2008). For airplanes identified in Boeing 

Alert Service Bulletin 737–53A1197, dated 

August 25, 2006: Do an ultrasound 

inspection of the slot-shaped cutout in the 

web for the door stop strap at stringer 16L, 

an HFEC inspection of the web along the 

upper and lower edges of the doubler around 

the doorstop strap at stringer 16L, and a 

detailed inspection of the web around the 

doubler for the cutout at stringer 16L, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1197, dated August 25, 2006, except 

as provided by paragraph (j)(4) of this AD. Do 

the inspections at the applicable time 

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

Boeing Alert Service Bulletin 737–53A1197, 

dated August 25, 2006, except as provided by 

paragraph (j)(2) of this AD. Do all applicable 

corrective actions before further flight in 

accordance with Boeing Alert Service 

Bulletin 737–53A1197, dated August 25, 

2006, except as provided by paragraph (j)(3) 

of this AD. Repeat the inspections at intervals 

not to exceed 4,500 flight cycles, until 

accomplishment of the repair/preventive 

change in accordance with Boeing Alert 

Service Bulletin 737–53A1197, dated August 

25, 2006, which terminates the repetitive 

inspections. 

(i) New Repetitive Inspections: Group 2 

Airplanes, Boeing Alert Service Bulletin 

737–53A1188, Revision 3, Dated September 

6, 2013 

For airplanes identified as Group 2 in 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013: At the 

applicable times specified in Table 3 of 

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

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013, except 

as required by paragraph (j)(1) of this AD: Do 

detailed and HFEC inspections for cracking 

in the web of the body station 303.9 frame 

at stringer 15L, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1188, Revision 3, 

dated September 6, 2013, except as required 

by paragraphs (j)(3) and (j)(4) of this AD. Do 

all applicable corrective actions before 

further flight. Repeat the inspection 

thereafter at the applicable time specified in 

Table 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013. 

Accomplishment of a repair using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD 

terminates the repetitive inspections required 

by this paragraph for the area covered by the 

repair. 

(j) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–53A1188, Revision 3, dated September 

6, 2013, specifies a compliance time ‘‘after 

the Revision 3 date of this service bulletin,’’ 

this AD requires compliance within the 

specified time after the effective date of this 

AD. 

(2) Where Boeing Alert Service Bulletin 

737–53A1197, dated August 25, 2006, 

specifies a compliance time ‘‘After the Date 

of this Service Bulletin,’’ this AD requires 

compliance for paragraph (h) of this AD 

within the specified time after September 23, 

2008 (the effective date of AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, August 

19, 2008)). For the initial inspection, the 

grace period for airplanes that have exceeded 

the specified threshold is extended to 4,500 

flight cycles after September 23, 2008 (the 

effective date of AD 2008–17–03). 

(3) Where Boeing Alert Service Bulletin 

737–53A1188, Revision 2, dated May 9, 2007; 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013; and 

Boeing Alert Service Bulletin 737–53A1197, 

dated August 25, 2006; specify to contact 

Boeing for appropriate action, including 

repair of damage outside the scope of the 

service information, repair using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(4) This AD does not require the specific 

access and restoration instructions identified 

in the Work Instructions of Boeing Alert 

Service Bulletin 737–53A1188, Revision 3, 

dated September 6, 2013; and Boeing Alert 

Service Bulletin 737–53A1197, dated August 

25, 2006. Operators may perform those 

actions in accordance with approved 

maintenance procedures. 

(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 

paragraph (l)(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 previously for AD 

2008–17–03, Amendment 39–15641 (73 FR 

48288, August 19, 2008), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(l) Related Information 

For more information about this AD, 

contact Nenita Odessa, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: 562–627– 

5234; fax: 562–627–5210; email: 

nenita.odessa@faa.gov. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on January 6, 2015. 

(i) Boeing Alert Service Bulletin 737– 

53A1188, Revision 3, dated September 6, 

2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on September 23, 2008 (73 

FR 48288, August 19, 2008). 

(i) Boeing Alert Service Bulletin 737– 

53A1188, Revision 2, dated May 9, 2007. 

(ii) Boeing Alert Service Bulletin 737– 

53A1197, dated August 25, 2006. 

(5) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

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71300 Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(6) You may view this service information 

at 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27362 Filed 12–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0776; Directorate 

Identifier 2009–NE–32–AD; Amendment 39– 

18007; AD 2010–17–11R2] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers Constant Speed Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising airworthiness 

directive (AD) 2010–17–11R1, which 

applies to all Dowty Propellers R408/6– 

123–F/17 model propellers. AD 2010– 

17–11R1 required initial application of 

sealant between the bus bar assembly 

and the backplate assembly of certain 

line-replaceable units (LRUs) and 

repetitive re-applications of sealant on 

all R408/6–123–F/17 model propellers. 

AD 2010–17–11R1 also provided an 

optional terminating action to the 

repetitive re-application of sealant. This 

AD increases the interval allowed 

between the required re-application of 

sealant, and specifies an additional 

acceptable sealant. This AD was 

prompted by failure of the propeller deice bus bar due to friction or contact 

between the bus bar and the backplate 

assembly, consequent intermittent short 

circuit, and possible double generator 

failure. We are issuing this AD to 

prevent an in-flight double generator 

failure, which could result in reduced 

control of the airplane. 

DATES: This AD is effective January 6, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 6, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Dowty 

Propellers, Anson Business Park, 

Cheltenham Road East, Gloucester GL2 

9QN, UK; phone: 44 0 1452 716000; fax: 

44 0 1452 716001. 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. 

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–2009– 

0776; 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 AD, the mandatory 

continuing airworthiness information, 

regulatory evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7761; fax 781–238–7170; email: 

michael.schwetz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2010–17–11R1, 

Amendment 39–17481 (78 FR 41283, 

July 10, 2013), (‘‘AD 2010–17–11R1’’). 

AD 2010–17–11R1 applied to the 

specified products. The NPRM 

published in the Federal Register on 

March 19, 2014 (79 FR 15269). The 

NPRM proposed to require increasing 

the interval allowed between the 

required re-application of sealant and 

specified an additional acceptable 

sealant. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request Correction to the Applicability 

and Compliance Paragraphs 

Horizon Air requested a correction in 

the Applicability and Compliance 

paragraphs for possible typographical 

errors between AD 2010–17–11R1 and 

the NPRM (79 FR 15269, March 19, 

2014). Horizon Air stated that the 

Applicability has changed from ‘‘. . . 

serial number (S/N) below DAP0327’’ in 

AD 2010–17–11R1 to ‘‘. . . S/N below 

DAP0927’’ in the proposed rule. With 

no discussion about the increased 

number of affected propellers, Horizon 

Air believes that typographical errors 

exist in the Applicability and 

Compliance sections. 

We do not agree. AD 2010–17–11R1 

required initial sealant application to all 

Dowty Propellers R408/6–123–F/17 

model propellers with a hub, actuator, 

and backplate assembly LRU S/Ns 

below DAP0347, not DAP0327 as 

quoted above. AD 2010–17–11R1 also 

required repetitive re-application of 

sealant for all LRU S/Ns below 

DAP0927. We did not change this AD. 

Request Change to Optional 

Terminating Action 

Horizon Air requested that all 

revisions to Dowty Propellers Service 

Bulletin (SB) No. D8400–61–94 be 

included in the Optional Terminating 

Action paragraph. The implied reason 

for this request was to support 

terminating action throughout the range 

of qualified SBs. 

We partially agree. We agree that 

Dowty Propellers SB No. D8400–61–94, 

Revision 6, dated December 12, 2013 

and earlier revisions provide adequate 

corrective actions to address the unsafe 

condition. We changed the Optional 

Terminating Action paragraph to 

include Dowty Propellers SB No. 

D8400–61–94, Revision 6, dated 

December 12, 2013 and earlier revisions. 

We do not agree that unknown future 

SB versions should be included in this 

AD. The content of future SB revisions 

is speculation. We did not change this 

AD to include all revisions of the SB. 

Request for Alternative Method of 

Compliance 

Horizon Air requested that we allow 

the use of 3M 4200 sealant as an 

equivalent replacement for the 3M 5300 

sealant. 

We agree. We approved 3M 4200 as 

an acceptable sealant in response to the 

Horizon Air comment to AD 2010–17– 

11R1 when that AD was at the NPRM 

stage; see 78 FR 41283, July 10, 2013. 

3M 4200 sealant is also one of three 

sealants identified in Dowty Propellers 

Alert Service Bulletin (ASB) No. D8400– 

mstockstill on DSK4VPTVN1PROD with RULES