74038 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules 

Revision A, dated December 4, 2012, to 

implement a reduction in service life of 

the ring gear carrier assembly, part 

number (P/N) 269A5194, from 6,000 

flight hours to 5,000 flight hours. 

Proposed AD Requirements 

This proposed AD would require 

reducing the life limit of the ring gear 

carrier assembly, P/N 269A5194, from 

6,000 hours TIS to 5,000 hours TIS by 

revising the Airworthiness Limitations 

section of the applicable maintenance 

manual. This proposed AD would also 

require replacing each ring gear carrier 

assembly with an airworthy ring gear 

carrier assembly on or before reaching 

5,000 hours TIS. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 16 helicopters of U.S. 

Registry. 

We estimate a minimal cost to change 

the life limit of the ring gear. If required, 

we estimate it would take 27.5 hours to 

replace a ring gear carrier assembly at 

$85 per work hour. Required parts 

would cost $7,591 for a total of $9,929 

per helicopter. 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Sikorsky Aircraft Corporation (Type 

Certificate Previously Held By 

Schweizer Aircraft Corporation): Docket 

No. FAA–2014–1020; Directorate 

Identifier 2013–SW–078–AD. 

(a) Applicability 

This AD applies to Sikorsky Aircraft 

Corporation Model 269D and Model 269D 

Configuration A helicopters with ring gear 

carrier assembly, part number (P/N) 

269A5194, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

fatigue crack in a ring gear carrier assembly. 

This condition could result in failure of the 

main rotor transmission, loss of engine power 

to the main rotor, and subsequent loss of 

control of the helicopter. 

(c) Comments Due Date 

We must receive comments by February 

13, 2015. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Before further flight: 

(1) Revise the Airworthiness Limitations 

Section of the applicable maintenance 

manual by reducing the life limit of the ring 

gear carrier assembly, P/N 269A5194, from 

6,000 hours time-in-service (TIS) to 5,000 

hours TIS. 

(2) Remove from service any ring gear 

carrier assembly, P/N 269A5194, with 5,000 

or more hours TIS. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, New York Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Norman Perenson, Aviation Safety Engineer, 

New York Aircraft Certification Office, 

Propulsion & Services Branch, FAA, 1600 

Stewart Ave., Westbury, New York; 

telephone (516) 228–7337; email 

Norman.Perenson@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

Sikorsky 269D Helicopter Alert Service 

Bulletin No. ASB DB–040A, Revision A, 

dated December 4, 2012, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Sikorsky Aircraft 

Corporation, Customer Service Engineering, 

124 Quarry Road, Trumbull, CT 06611; 

telephone 1–800–Winged–S or 203–416– 

4299; email sikorskywcs@sikorsky.com. You 

may review a copy of information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300 Main Rotor Drive System. 

Issued in Fort Worth, Texas, on December 

8, 2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–29260 Filed 12–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0921; Directorate 

Identifier 2014–NM–073–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules 74039 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–14– 

05, which applies to certain The Boeing 

Company Model 747–400 and 747–400F 

series airplanes. AD 2013–14–05 

currently requires repetitive inspections 

of the longeron extension fittings for 

cracking, and related investigative and 

corrective actions if necessary. AD 

2013–14–05 also provides optional 

terminating action for the repetitive 

inspections. Since we issued AD 2013– 

14–05, we determined that more work is 

necessary on airplanes on which a 

terminating action (permanent repair, 

longeron extension fitting replacement, 

or modification) was accomplished. 

This proposed AD would continue to 

require the requirements of AD 2013– 

14–05, and would add new repetitive 

high frequency eddy current (HFEC) 

inspections of any modified, repaired, 

or replaced longeron extension fitting 

for cracking, and applicable related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct cracks in the longeron 

extension fittings, which can become 

large and adversely affect the structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 29, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

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– 

0921; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6428; 

fax: 425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0921; Directorate Identifier 

2014–NM–073–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 25, 2013, we issued AD 

2013–14–05, Amendment 39–17510 (78 

FR 43763, July 22, 2013), for certain the 

Boeing Company Model 747–400 and 

747–400F series airplanes. AD 2013–14– 

05 requires repetitive inspections of the 

longeron extension fittings for cracking, 

and related investigative and corrective 

actions if necessary. AD 2013–14–05 

also provides for optional terminating 

action for the repetitive inspections. AD 

2013–14–05 resulted from reports of 

cracking in the outboard flange of the 

longeron extension fittings, which 

attach to the wing-to-body fairing 

support frame. We issued AD 2013–14– 

05 to detect and correct cracks in the 

longeron extension fittings, which can 

become large and adversely affect the 

structural integrity of the airplane. 

Actions Since AD 2013–14–05, 

Amendment 39–17510 (78 FR 43763, 

July 22, 2013) Was Issued 

Since we issued AD 2013–14–05, 

Amendment 39–17510 (78 FR 43763, 

July 22, 2013), we determined that more 

work is necessary on airplanes that 

accomplished a permanent repair, 

longeron extension fitting replacement, 

or preventive modification (the 

terminating actions specified in AD 

2013–14–05). 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–53A2860, Revision 1, 

dated March 18, 2014. For information 

on the procedures and compliance 

times, see this service information at 

http://www.regulations.gov by searching 

for Docket No. FAA–2014–0921. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2013–14–05, Amendment 39–17510 (78 

FR 43763, July 22, 2013), this proposed 

AD would retain all of the requirements 

of AD 2013–14–05. Those requirements 

are referenced in the service information 

identified previously, which, in turn, is 

referenced in paragraphs (g), (h)(1), and 

(j) of this proposed AD. This proposed 

AD would require additional repetitive 

HFEC inspections of the left and right 

longeron extension fittings for cracking, 

and applicable related investigative and 

corrective actions, for airplanes that 

have previously accomplished a 

permanent repair, longeron extension 

fitting replacement, or preventive 

modification, as identified in Boeing 

Alert Service Bulletin 747–53A2860, 

dated December 4, 2012. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 


tkelley on DSK3SPTVN1PROD with PROPOSALS
74040 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Differences Between This Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 747– 

53A2860, Revision 1, dated March 18, 

2014, 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. 

Clarification of Terminating Actions for 

Certain Inspections 

Paragraph (h)(1) of this proposed AD 

specifies that if the terminating action is 

done ‘‘before the effective date of this 

AD’’ in accordance with the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2860, 

dated December 4, 2012, it terminates 

the inspections in paragraph (g) of this 

proposed AD. In paragraph (h)(2) of this 

proposed AD we specify that the 

terminating action if done ‘‘on or after 

the effective date of this AD’’ must be 

done in accordance with the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014, 

except as required by paragraph (k)(2) of 

this AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 41 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 

HFEC inspection [retained action from 

AD 2013-14-05, Amendment 39-17510 

(78 FR 43763, July 22, 2013)].

32 work-hours × $85 per hour = $2,720 

per inspection cycle.

$0 $2,720 per inspection cycle.$111,520 per inspection cycle. 

Terminating action for certain inspections 

[retained action from AD 2013-14-05, 

Amendment 39-17510 (78 FR 43763, 

July 22, 2013)].

479 work-hours × $85 per hour = 

$40,715.

0 $40,715 .................. $1,669,315. 

HFEC inspection [new action] .................. 32 work-hours × $85 per hour = $2,720 

per inspection cycle.

0 $2,720 per inspection cycle.$111,520 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 this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 464 work-hours × $85 per hour = $39,440 ............................................... $0 $39,440 

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 have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules 74041 

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) 

2013–14–05, Amendment 39–17510 (78 

FR 43763, July 22, 2013), and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2014–0921; Directorate Identifier 2014– 

NM–073–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by January 29, 2015. 

(b) Affected ADs 

This AD replaces AD 2013–14–05, 

Amendment 39–17510 (78 FR 43763, July 22, 

2013). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 and –400F series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the outboard flange of the 

longeron extension fittings, and we 

determined that more work is necessary on 

airplanes on which a permanent repair, 

longeron extension fitting replacement, or 

modification was accomplished, as required 

by AD 2013–14–05, Amendment 39–17510 

(78 FR 43763, July 22, 2013) could crack. We 

are issuing this AD to detect and correct 

cracks in the longeron extension fittings, 

which can become large and adversely affect 

the structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable time specified in table 1 

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

Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014: Do surface 

high frequency eddy current (HFEC) 

inspections for cracking of the left and right 

longeron extension fittings, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014, except as 

required by paragraph (k)(2) of this AD. Do 

all applicable corrective actions at the 

applicable time specified in table 1 of 

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

Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014. If no 

cracking is found, repeat the inspection 

thereafter at the intervals specified in table 1 

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

Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014, until a 

terminating action specified in paragraph (h) 

of this AD is done. 

(h) Terminating Actions for the Inspections 

Required by Paragraph (g) of This AD 

(1) Doing the permanent repair, longeron 

extension fitting replacement, or preventative 

modification before the effective date of this 

AD, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

terminates the repetitive inspections required 

by paragraph (g) of this AD. Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012, was incorporated by 

reference in AD 2013–14–05, Amendment 

39–17510 (78 FR 43763, July 22, 2013). After 

accomplishing the actions specified in this 

paragraph, the actions specified in paragraph 

(i) of this AD must be done at the times 

specified in paragraph (i) of this AD. 

(2) Doing the repair (PART 4 of Boeing 

Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014), longeron 

extension fitting replacement, or 

modification on or after the effective date of 

this AD, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2860, Revision 1, 

dated March 18, 2014, except as required by 

paragraph (k)(2) of this AD, terminates the 

repetitive inspection requirements of 

paragraph (g) of this AD. After accomplishing 

the actions specified in this paragraph, the 

actions specified in paragraph (i) of this AD 

must be done at the times specified in 

paragraph (i) of this AD. 

(i) Post-Modification/Repair/Replacement 

Inspections 

For airplanes on which any action 

identified in paragraph (h) of this AD has 

been accomplished (including if done as a 

corrective action required by paragraph (g) or 

(j) of this AD): At the applicable time 

specified in table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2860, Revision 1, dated 

March 18, 2014, except as required by 

paragraph (k)(1) of this AD, do a HFEC 

inspection of the left and right longeron 

extension fittings for cracking, as applicable, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2860, Revision 1, dated March 18, 

2014. Do all applicable corrective actions at 

the applicable time specified in table 3 of 

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

Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014, except as 

required by paragraph (k)(2) of this AD. If no 

cracking is found, repeat the inspection 

thereafter at the interval specified in table 3 

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

Alert Service Bulletin 747–53A2860, 

Revision 1, dated March 18, 2014. 

(j) Inspection of Temporary Repair and 

Corrective Actions 

For airplanes on which a temporary repair 

as specified in Boeing Alert Service Bulletin 

747–53A2860 has been done: At the times 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2860, Revision 1, dated 

March 18, 2014, do a surface HFEC 

inspection of the temporary repair of the 

longeron extension fittings for cracking, and 

do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2860, Revision 1, dated March 18, 

2014, except as required by paragraph (k)(2) 

of this AD. Do all applicable corrective 

actions before further flight. 

(k) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2860, Revision 1, dated March 18, 

2014, specifies a compliance time ‘‘after the 

Revision 1 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2860, Revision 1, dated March 18, 

2014, specifies to contact Boeing for repair 

information: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (m) of 

this AD. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (g) and (j) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 747–53A2860, 

dated December 4, 2012, which was 

incorporated by reference in AD 2013–14–05, 

Amendment 39–17510 (78 FR 43763, July 22, 

2013). 

(m) 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 (m)(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 

2013–14–05, Amendment 39–17510 (78 FR 

43763, July 22, 2013), are approved as 

AMOCs for the corresponding provisions of 

paragraphs (g), (h), and (j) of this AD. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
74042 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules 

(n) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 425– 

917–6590; email: Nathan.P.Weigand@

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. For 

information on the availability of this 

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

Issued in Renton, Washington, on 

December 5, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–29232 Filed 12–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2014–0869; Airspace 

Docket No. 14–AWP–6] 

Proposed Establishment of Class E 

Airspace; Hazen, NV 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish Class E airspace at the Hazen 

VHF Omni-Directional Radio Range 

Tactical Air Navigation Aid (VORTAC), 

Hazen, NV, to facilitate vectoring of 

Instrument Flight Rules (IFR) aircraft 

under control of Oakland Air Route 

Traffic Control Center (ARTCC). The 

FAA is proposing this action to enhance 

the safety and management of aircraft 

operations within the National Airspace 

System. 

DATES: Comments must be received on 

or before January 29, 2015. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590; telephone (202) 

366–9826. You must identify FAA 

Docket No. FAA–2014–0869; Airspace 

Docket No. 14–AWP–6, at the beginning 

of your comments. You may also submit 

comments through the Internet at 

http://www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Steve Haga, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue SW., Renton, WA 98057; 

telephone (425) 203–4563. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA– 

2014–0869 and Airspace Docket No. 14– 

AWP–6) and be submitted in triplicate 

to the Docket Management System (see 

ADDRESSES section for address and 

phone number). You may also submit 

comments through the Internet at 

http://www.regulations.gov. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

on this action must submit with those 

comments a self-addressed stamped 

postcard on which the following 

statement is made: ‘‘Comments to FAA 

Docket No. FAA–2014–0869 and 

Airspace Docket No. 14–AWP–6’’. The 

postcard will be date/time stamped and 

returned to the commenter. 

All communications received on or 

before the specified closing date for 

comments will be considered before 

taking action on the proposed rule. The 

proposal contained in this action may 

be changed in light of comments 

received. All comments submitted will 

be available for examination in the 

public docket both before and after the 

closing date for comments. A report 

summarizing each substantive public 

contact with FAA personnel concerned 

with this rulemaking will be filed in the 

docket. 

Availability of NPRM’s 

An electronic copy of this document 

may be downloaded through the 

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

Recently published rulemaking 

documents can also be accessed through 

the FAA’s Web page at http://

www.faa.gov/airports_airtraffic/air_

traffic/publications/airspace_

amendments/. 

You may review the public docket 

containing the proposal, any comments 

received, and any final disposition in 

person in the Dockets Office (see the 

ADDRESSES section for the address and 

phone number) between 9:00 a.m. and 

5:00 p.m., Monday through Friday, 

except federal holidays. An informal 

docket may also be examined during 

normal business hours at the Northwest 

Mountain Regional Office of the Federal 

Aviation Administration, Air Traffic 

Organization, Western Service Center, 

Operations Support Group, 1601 Lind 

Avenue SW., Renton, WA 98057. 

Persons interested in being placed on 

a mailing list for future NPRM’s should 

contact the FAA’s Office of Rulemaking, 

(202) 267–9677, for a copy of Advisory 

Circular No. 11–2A, Notice of Proposed 

Rulemaking Distribution System, which 

describes the application procedure. 

The Proposal 

The FAA is proposing an amendment 

to Title 14 Code of Federal Regulations 

(14 CFR) Part 71 by establishing Class E 

en route domestic airspace extending 

upward from 1,200 feet above the 

surface at the Hazen VORTAC 

navigation aid, Hazen, NV. This action 

would contain aircraft while in IFR 

conditions under control of Oakland 

ARTCC by vectoring aircraft from en 

route airspace to terminal areas. 

Class E airspace designations are 

published in paragraph 6006, of FAA 

Order 7400.9Y, dated August 6, 2014, 

and effective September 15, 2014, which 

is incorporated by reference in 14 CFR 

71.1. The Class E airspace designation 

listed in this document will be 

published subsequently in this Order. 

The FAA has determined this 

proposed regulation only involves an 

established body of technical 

regulations for which frequent and 

routine amendments are necessary to 

keep them operationally current. 

Therefore, this proposed regulation: (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); and (3) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified this proposed rule, when 

promulgated, would not have a 

significant economic impact on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the U.S. Code. Subtitle 1, 


tkelley on DSK3SPTVN1PROD with PROPOSALS