35966 Federal Register / Vol. 79, No. 122 / Wednesday, June 25, 2014 / Proposed Rules 

her knowledge, true, accurate, and 

complete. 

(c) Review. Unless a referral is made 

under paragraph (e) of this section, SBA 

will decide within 10 business days of 

receiving a small business status 

advisory opinion to accept or reject it 

based on its consistency with this part. 

SBA will provide written notification of 

that decision to the SBDC or PTAC that 

issued the small business status 

advisory opinion as well as to the 

covered concern. 

(d) Reliance. A concern that receives 

a small business status advisory opinion 

holding that it does not exceed the 

applicable size standard(s) may rely 

upon that determination for purposes of 

responding to federal procurement 

opportunities from the date it is issued 

unless and until that advisory opinion 

is rejected by SBA in accordance with 

paragraph (c) of this section or 

§ 121.1009. 

(e) Referral for Size Determination. 

Nothing in this section precludes SBA 

from requesting a formal size 

determination for a concern that is the 

subject of a small business status 

advisory opinion pursuant to 

§ 121.1001(b)(9). 

■ 5. Amend § 121.1001 by revising 

paragraph (b)(9) to read as follows: 

§ 121.1001 Who may initiate a size protest 

or request a formal size determination? 

* * * * * 

(b) * * * 

(9) For other purposes related to 

protecting the integrity of the Federal 

procurement process, including 

validating that firms listed in the 

System for Award Management database 

are small and firms can rely upon 

advisory size status opinions, the 

Government Contracting Area Director 

or the Director, Office of Government 

Contracting may initiate a formal size 

determination when sufficient 

information exists that calls into 

question a firm’s small business status. 

The current date will be used to 

determine size, and SBA will initiate 

the process to remove from the database 

the small business designation of any 

firm found to be other than small. 

* * * * * 

Maria Contreras-Sweet, 

Administrator. 

[FR Doc. 2014–14337 Filed 6–24–14; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0343; Directorate 

Identifier 2014–NM–077–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 747–8 and 

747–8F series airplanes. This proposed 

AD was prompted by an analysis by the 

manufacturer, which revealed that 

certain fuse pins for the strut-to-wing 

attachment of the outboard aft upper 

spar are susceptible to migration in the 

event of a failed fuse pin through bolt. 

This proposed AD would require 

replacing the fuse pins for the strut-towing attachment of the outboard aft 

upper spar with new fuse pins, and 

replacing the access cover assemblies 

with new access cover assemblies. We 

are proposing this AD to prevent 

migration of these fuse pins, which 

could result in the complete disconnect 

and loss of the strut-to-wing attachment 

load path for the outboard aft upper 

spar. The complete loss of an outboard 

aft upper spar strut-to-wing attachment 

load path could result in divergent 

flutter in certain parts of the flight 

envelope, which could result in loss of 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 11, 2014. 

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 98057–3356. 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– 

0343; 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: 

Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6513; 

fax: 425–917–6590; email: 

narinder.luthra@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– 

2014–0343; Directorate Identifier 2014– 

NM–077–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 

An analysis by Boeing revealed that 

the fuse pins for the strut-to-wing 

attachment of the outboard aft upper 

spar on struts Nos. 1 and 4 are 

susceptible to migration in the event of 

a failed fuse pin through bolt. To 

prevent these fuse pins from migrating 


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Federal Register / Vol. 79, No. 122 / Wednesday, June 25, 2014 / Proposed Rules 35967 

outboard, the design of the fuse pins 

was changed to add a flange. The design 

of the outboard fuse pin access cover 

assemblies was also changed by adding 

interference ribs so a fuse pin can be 

installed only with the flanged end of 

the fuse pin on the inboard side of the 

outboard aft upper spar fitting. 

Migration of the fuse pins for the strutto-wing attachment of the outboard aft 

upper spar on struts Nos. 1 and 4 could 

result in the complete disconnect and 

loss of the strut-to-wing attachment load 

path for the outboard aft upper spar. 

The complete loss of the No. 1 or No. 

4 outboard aft upper spar strut-to-wing 

attachment load path could result in 

divergent flutter in certain parts of the 

flight envelope, which could result in 

loss of control of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–54A2238, dated January 

31, 2014. For information on the 

procedures and compliance times, see 

this service information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0343. 

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. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee, to enhance the 

AD system. One enhancement was a 

new process for annotating which steps 

in the service information are required 

for compliance with an AD. 

Differentiating these steps from other 

tasks in the service information is 

expected to improve an owner’s/

operator’s understanding of crucial AD 

requirements and help provide 

consistent judgment in AD compliance. 

The actions specified in the service 

information described previously 

include steps that are labeled as RC 

because these steps have a direct effect 

on detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

As noted in the specified service 

information, steps labeled as RC must be 

done to comply with the proposed AD. 

However, steps that are not labeled as 

RC are recommended. Those steps that 

are not labeled as RC may be deviated 

from, done as part of other actions, or 

done using accepted methods different 

from those identified in the service 

information without obtaining approval 

of an alternative method of compliance 

(AMOC), provided the steps labeled as 

RC can be done and the airplane can be 

put back in a serviceable condition. Any 

substitutions or changes to steps labeled 

as RC will require approval of an 

alternative method of compliance. 

Costs of Compliance 

We estimate that this proposed AD 

affects 5 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 

Replacement ........................................ 97 work-hours × $85 per hour = $8,245 ................... $31,076 $39,321 $196,605 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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– 

2014–0343; Directorate Identifier 2014– 

NM–077–AD. 

(a) Comments Due Date 

We must receive comments by August 11, 

2014. 


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35968 Federal Register / Vol. 79, No. 122 / Wednesday, June 25, 2014 / Proposed Rules 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–8 and 747–8F series airplanes; 

certificated in any category; having a Variable 

Number identified in paragraph 1.A., 

‘‘Effectivity,’’ of Boeing Alert Service Bulletin 

747–54A2238, dated January 31, 2014; and 

Variable Number RC573. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by an analysis by 

the manufacturer, which revealed that the 

fuse pins for the strut-to-wing attachment of 

the outboard aft upper spar on struts Nos. 1 

and 4 are susceptible to migration in the 

event of a failed fuse pin through bolt. We 

are issuing this AD to prevent migration of 

the fuse pins for the strut-to-wing attachment 

of the outboard aft upper spar on struts Nos. 

1 and 4, which could result in the complete 

disconnect and loss of the strut-to-wing 

attachment load path for the outboard aft 

upper spar. The complete loss of the No. 1 

or No. 4 outboard aft upper spar strut-to-wing 

attachment load path could result in 

divergent flutter in certain parts of the flight 

envelope, which could result in loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of Fuse Pins and Access 

Cover Assemblies 

Within 48 months after the effective date 

of this AD: Replace the fuse pins for the 

outboard aft upper spar and the access cover 

assemblies on struts Nos. 1 and 4, with new 

fuse pins and access cover assemblies, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2238, dated January 31, 2014. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (i)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) 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) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(i) Related Information 

(1) For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6513; fax: 425–917– 

6590; email: narinder.luthra@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

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

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356. For information on the availability of 

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

Issued in Renton, Washington, on June 17, 

2014. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–14814 Filed 6–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0342; Directorate 

Identifier 2014–NM–007–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 747–400, 

747–400D, 747–400F, 747–8F, and 747– 

8 series airplanes. This proposed AD 

was prompted by reports of very high 

temperatures, up to 67 degrees Celsius 

(152 degrees Fahrenheit), near the floor 

in the aft lower lobe cargo compartment. 

This proposed AD would require 

installing an additional zone 

temperature sensor (ZTS) in the aft 

cargo compartment. For certain 

airplanes, the proposed AD would first 

require installing tape and replacing the 

markers in the bulk cargo compartment, 

unless terminated by the early 

installation of the ZTS. We are 

proposing this AD to prevent 

overheating of the aft lower lobe cargo 

compartment, where, if temperature 

sensitive cargo is present, the release of 

flammable vapors could result in a fire 

or explosion if exposed to an ignition 

source. 

DATES: We must receive comments on 

this proposed AD by August 11, 2014. 

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. 

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– 

0342; 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 


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