36258 Federal Register / Vol. 80, No. 121 / Wednesday, June 24, 2015 / Proposed Rules 

(2) This paragraph provides credit for 

inspections required by paragraphs (g)(1) and 

(g)(2) of this AD, if those inspections were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 747– 

53A2450, Revision 7, dated November 2, 

2011, which was incorporated by reference in 

AD 2013–17–08, Amendment 39–17572 (78 

FR 57053, September 17, 2013). 

(j) 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 (k)(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 for AD 2005–01–09, 

Amendment 39–13933 (70 FR 1340, January 

7, 2005), are approved as AMOCs for the 

corresponding provisions of paragraph (g)(1) 

of this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

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, Washington. 

For information on the availability of this 

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

Issued in Renton, Washington, on June 12, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–15400 Filed 6–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1983; Directorate 

Identifier 2015–NM–020–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 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This proposed AD was 

prompted by a report of a crack of the 

forward leg of the left front spar lower 

chord and cracks on the lower wing skin 

at three fastener holes common to the 

nacelle outboard side load fitting. This 

proposed AD would require repetitive 

inspections for cracks on the front spar 

lower chord, inspar skin, and wing skin, 

and corrective action if necessary. We 

are proposing this AD to detect and 

correct fatigue cracking of the forward 

leg of the front spar lower chord, inspar 

skin, and wing skin common to the 

nacelle outboard side load fitting, which 

could adversely affect the structural 

integrity of the wing. 

DATES: We must receive comments on 

this proposed AD by August 10, 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA 2015– 

1983. 

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–2015– 

1983; 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6450; fax: 

425–917–6590; email: alan.pohl@

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– 

2015–1983; Directorate Identifier 2015– 

NM–020–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We received a report of a crack on the 

forward leg of the left front spar lower 

chord at wing buttock line (WBL) 177. 

The front spar lower chord was 

removed, repaired, and reinstalled. 

Upon additional inspection of the 

repaired spar chord installation, cracks 

were also discovered on the lower wing 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 121 / Wednesday, June 24, 2015 / Proposed Rules 36259 

skin at three fastener holes common to 

the nacelle outboard side load fitting at 

WBL 198.6. These cracks were 

identified on an airplane that had 

accumulated 57,617 total flight cycles. 

Metallurgical analysis of the chord 

determined that cracks initiated at 

fastener holes and were propagated by 

operating load fatigue. The analysis 

found no anomalies that could have 

contributed to the cracking. Fatigue 

cracking of the forward leg of the left 

front spar lower chord, inspar skin, and 

lower wing skin common to the nacelle 

outboard side load fitting, if not 

corrected, could adversely affect the 

structural integrity of the wing. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–57A1323, dated December 

5, 2014. The service information 

describes procedures for repetitive 

inspections for cracks on the left and 

right wing front spar lower chord, 

inspar skin, and wing skin and 

corrective action if necessary. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this NPRM. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ Refer to 

this service information for details on 

the procedures and compliance times. 

The phrase ‘‘corrective actions’’ is 

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 This Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 737– 

57A1323, dated December 5, 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. 

For Group 2 and 3 airplanes identified 

in Boeing Alert Service Bulletin 737– 

57A1323, dated December 5, 2014, 

paragraph (h) of this proposed AD 

specifies repeating the detailed 

inspection for cracks on the left and 

right wing front spar lower chord and 

inspar skin inspection, except in areas 

repaired in accordance with the 

procedures specified in paragraph (k) of 

this AD. 

Explanation of Required for 

Compliance (RC) Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), 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 steps identified as RC 

(required for compliance) in any service 

information identified previously have a 

direct effect on detecting, preventing, 

resolving, or eliminating an identified 

unsafe condition. 

For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the following 

provisions apply: (1) The steps labeled 

as RC, including substeps under an RC 

step and any figures identified in an RC 

step, must be done to comply with the 

AD, and an AMOC is required for any 

deviations to RC steps, including 

substeps and identified figures; and (2) 

steps not labeled as RC may be deviated 

from using accepted methods in 

accordance with the operator’s 

maintenance or inspection program 

without obtaining approval of an 

AMOC, provided the RC steps, 

including substeps and identified 

figures, can still be done as specified, 

and the airplane can be put back in an 

airworthy condition. 

Costs of Compliance 

We estimate that this proposed AD 

affects 331 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 (28 Group 2 

airplanes).

7 work-hours × $85 per hour = $595 per inspection cycle.$0 $595 per inspection 

cycle.

$16,660 per inspection 

cycle. 

Inspection and fastener 

installation (302 

Group 3 airplanes).

Up to 94 work-hours × $85 per hour = $7,990 

per inspection cycle.

0 Up to $7,990 per inspection cycle.Up to $2,412,980 per 

inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the actions specified for 

the Group 1 airplane in this proposed 

AD. 

We also 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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
36260 Federal Register / Vol. 80, No. 121 / Wednesday, June 24, 2015 / Proposed Rules 

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– 

2015–1983; Directorate Identifier 2015– 

NM–020–AD. 

(a) Comments Due Date 

We must receive comments by August 10, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

crack in the forward leg of the left front spar 

lower chord and cracks on the lower wing 

skin at three fastener holes common to the 

nacelle outboard side load fitting. We are 

issuing this AD to detect and correct fatigue 

cracking of the forward leg of the front spar 

lower chord, inspar skin, and wing skin 

common to the nacelle outboard side load 

fitting, which could adversely affect the 

structural integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions for 

Group 1 Airplanes 

For Group 1 airplanes identified in Boeing 

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014: Within 120 days after the 

effective date of this AD, do inspections of 

the left and right wing front spar lower chord 

and inspar skin, and the left and right wing 

nacelle outboard side load fitting fastener 

holes common to the front spar lower chord 

and skin, and do all applicable corrective 

actions, using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(h) Repetitive Detailed Inspections and 

Corrective Actions 

For Group 2 and 3 airplanes identified in 

Boeing Alert Service Bulletin 737–57A1323, 

dated December 5, 2014: Except as provided 

by paragraph (j)(1) of this AD, at the 

applicable time specified in Table 1 of 

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

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014, do a detailed inspection 

for cracks on the left and right wing front 

spar lower chord and inspar skin, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–57A1323, 

dated December 5, 2014, except as specified 

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

applicable corrective actions before further 

flight. Repeat the inspection thereafter at the 

applicable interval specified in Table 1 of 

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

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014, except in areas repaired in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(i) Repetitive High Frequency Eddy Current 

(HFEC) Inspections and Corrective Actions 

For Group 3 airplanes identified in Boeing 

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014: Except as provided by 

paragraph (j)(1) of this AD, at the applicable 

time specified in Table 2 or Table 3 of 

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

Alert Service Bulletin 737–57A1323, dated 

December 5, 2014, do the actions specified in 

paragraphs (i)(1) or (i)(2) of this AD. Repeat 

the inspection specified in either paragraph 

(i)(1) or (i)(2) of this AD thereafter at the 

applicable interval specified in Table 2 or 

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

Boeing Alert Service Bulletin737–57A1323, 

dated December 5, 2014. 

(1) Do an HFEC open hole probe inspection 

for cracks of the left and right wing nacelle 

outboard side load fitting fastener holes 

common to the front spar lower chord and 

skin, and perform all applicable corrective 

actions, in accordance with Part 2, Option 1 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–57A1323, 

dated December 5, 2014, except as provided 

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

applicable corrective actions before further 

flight. 

(2) Do an HFEC surface probe inspection 

for cracks in the wing inspar skin, and 

perform all applicable corrective actions, in 

accordance with Part 2, Option 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–57A1323, dated 

December 5, 2014, except as provided by 

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

corrective actions before further flight. 

(j) Exceptions to Service Information 

Specifications 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–57A1323, 

dated December 5, 2014, specifies a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time ‘‘after the effective date of this AD.’’ 

(2) Although Boeing Alert Service Bulletin 

737–57A1323, dated December 5, 2014, 

specifies to contact Boeing for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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-LAACO-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 that has been 

authorized by the Manager, Los Angeles 

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) Except as required by paragraph (j)(2) 

of this AD: For service information that 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 121 / Wednesday, June 24, 2015 / Proposed Rules 36261 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(4)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition 

(l) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6450; fax: 425–917–6590; 

email: alan.pohl@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 June 12, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–15398 Filed 6–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–1622; Airspace 

Docket No. 15–AWP–9] 

Proposed Amendment of Class D and 

Class E Airspace; Stockton, CA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

modify Class D airspace, Class E surface 

area airspace, and Class E airspace 

extending upward from 700 feet above 

the surface, at Stockton Metropolitan 

Airport, Stockton, CA. After a biennial 

review, and the decommissioning of the 

Manteca VHF omnidirectional radio 

range and distance measuring 

equipment (VOR/DME), the FAA found 

it necessary to amend the airspace areas 

for the safety and management of 

Instrument Flight Rules (IFR) operations 

for Standard Instrument Approach 

Procedures (SIAPs) at the airport. 

DATES: Comments must be received on 

or before August 10, 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–2015–1622; Airspace 

Docket No. 15–AWP–9, at the beginning 

of your comments. You may also submit 

comments through the Internet at 

http://www.regulations.gov. You may 

review the public docket containing the 

proposal, any comments received, and 

any final disposition in person in the 

Dockets Office between 9:00 a.m. and 

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

except Federal holidays. The Docket 

Office (telephone 1–800–647–5527), is 

on the ground floor of the building at 

the above address. 

FAA Order 7400.9Y, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

online at http://www.faa.gov/air_traffic/ 

publications/. The Order is also 

available for inspection 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/

code_of_federal-regulations/ibr_

locations.html. 

FAA Order 7400.9, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. For further information, 

you can contact the Airspace Policy and 

Regulations Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

FOR FURTHER INFORMATION CONTACT: Rob 

Riedl, Federal Aviation Administration, 

Operations Support Group, Western 

Service Center, 1601 Lind Avenue SW., 

Renton, WA 98057; telephone (425) 

203–4534. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

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

Section 106, describes the authority for 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the agency’s 

authority. This rulemaking is 

promulgated under the authority 

described in Subtitle VII, Part A, 

Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of the airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority as it would 

amend controlled airspace at Stockton 

Metropolitan Airport, Stockton, CA. 

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 and be submitted in 

triplicate to the address listed above. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

on this notice must submit with those 

comments a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2015–1622/Airspace 

Docket No. 15–AWP–9.’’ The postcard 

will be date/time stamped and returned 

to the commenter. 

Availability of NPRMs 

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 NPRMs should 

contact the FAA’s Office of Rulemaking, 

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

Circular No. 11–2A, Notice of Proposed 


tkelley on DSK3SPTVN1PROD with PROPOSALS