Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules 22943 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided the MLG remains extended 

throughout the flight. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2014–0058, dated 

March 11, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2015–0831. 

(2) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(3) For Messier-Bugatti-Dowty service 

information identified in this AD, contact 

Messier Services Americas, Customer 

Support Center, 45360 Severn Way, Sterling, 

VA 20166 8910; phone: 703–450–8233; fax: 

703–404–1621; Internet: https://

techpubs.services/messier-dowty.com. 

(4) You may view this 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 April 9, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–09288 Filed 4–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0926; Directorate 

Identifier 2014–NM–121–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 97–07–14, 

for certain Airbus Model A320–111, 

–211, and –231 airplanes. AD 97–07–14 

currently requires modification of an 

area on the front spar of the wing center 

section by installing shims and new 

fasteners to reinforce pressure floor 

fittings. Since we issued AD 97–07–14, 

we have determined the need for 

repetitive inspections on airplanes on 

which the modification of the rib flange 

on the front spar of the wing center 

section has been done. This proposed 

AD would continue to require 

modifying the rib flange on the front 

spar of the wing center section by 

installing shims and new fasteners to 

reinforce pressure floor fittings; and 

would require repetitive high frequency 

eddy current inspections for cracking of 

the radius of the rib flanges and vertical 

stiffener at frame 36, a rototest 

inspection for cracking of the fastener 

holes of the rib flanges, repair if needed, 

and adding additional airplanes to the 

applicability. We are proposing this AD 

to prevent fatigue cracking on the rib 

flange area of the front spar of the wing 

center section, which can reduce the 

structural integrity of fuselage frame 36 

and the wing center section. 

DATES: We must receive comments on 

this proposed AD by June 8, 2015. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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–2015– 

0926; 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 Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

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–2015–0926; Directorate Identifier 

2014–NM–121–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 based on 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 March 27, 1997, we issued AD 97– 

07–14, Amendment 39–9988 (62 FR 

16473, April 7, 1997). AD 97–07–14 

requires modification of an area on the 

front spar of the wing center section by 

installing shims and new fasteners to 

reinforce pressure floor fittings on 

certain Airbus Model A320–111, –211 

and –231 airplanes. 

Since we issued AD 97–07–14, 

Amendment 39–9988 (62 FR 16473, 

April 7, 1997), we have determined the 

need for repetitive inspections on 

airplanes on which Airbus Modification 

20976 (modification of the rib flange on 

the front spar of the wing center section) 

was done in production, or was done 

using Airbus Service Bulletin A320–57– 

1013, dated April 12, 1989; or Airbus 

Service Bulletin A320–57–1013, 

Revision 1, dated September 29, 1992. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 


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for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0053, dated March 7, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on certain Airbus 

Model A320–211 and –231 airplanes. 

The MCAI states: 

During full scale fatigue tests on the Airbus 

A320 test specimen, cracks were found in the 

rib flange on the front spar side 

perpendicular to vertical posts at frame (FR) 

36. It was determined that similar cracks 

could develop on certain in-service 

aeroplanes. 

This condition, if not detected and 

corrected, could affect the wing structural 

integrity. 

To reduce the risk of crack initiation, two 

modifications for aeroplanes in production 

and one modification for in-service 

aeroplanes were developed by Airbus: Prior 

to [manufacturer serial number] MSN 0085, 

the adaptation modification (Mod) 20976 was 

applied in production, consisting in 

installing shims under the fasteners linking 

the rib flange, the lower corner, the front spar 

and its vertical stiffener; from MSN 0085 

onwards, the serial Mod 20908 was applied 

in production, consisting in installing 

reinforced lower surface rib flanges at front 

spar level. 

Airbus issued Service Bulletin (SB) A320– 

57–1013 for affected in-service aeroplanes, 

and [Directorate General for Civil Aviation] 

DGAC France issued AD 95–098–066 [which 

corresponds to FAA AD 97–07–14, 

Amendment 39–9988, (62 FR 16473, April 7, 

1997)] to require installation of shims under 

the fasteners linking the rib flange, the lower 

corner, the front spar and its vertical 

stiffener. 

Following a recent analysis, Airbus 

identified the need for repetitive [HFEC and 

rototest] inspections for aeroplanes on which 

Airbus SB A320–57–1013 or production Mod 

20976 has been embodied. 

For the reason described above, this 

[EASA] AD retains the requirements of DGAC 

France AD 95–098–066, which is superseded, 

and requires repetitive [HFEC and rototest] 

inspections of the center wing lower ribs at 

FR 36 and, depending on findings, 

accomplishment of a repair. 

After EASA issued PAD 14–013, it was 

discovered that additional work [removal of 

shims and fasteners on the rib flange on the 

front spar side and doing an HFEC inspection 

for cracking of the radius of the rib flanges 

and a rototest inspection for cracking of the 

fastener holes during each inspection] to be 

included in Revision 01 of Airbus SB A320– 

57–1175, is required to accomplish the 

inspections. This Final [EASA] AD has been 

amended accordingly. 

Airplanes having MSNs 001, 009, and 

015 were not included in the 

applicability of AD 97–07–14, 

Amendment 39–9988 (62 FR 16473, 

April 7, 1997). EASA AD 2014–0053, 

dated March 7, 2014, expanded the 

applicability to all airplanes having up 

to MSN 0084. We included paragraph 

(h) of this proposed AD to require the 

modification for the airplanes having 

MSNs 001, 009, and 015.You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0926. 

Related Service Information Under 1 

CFR part 51 

Airbus has issued Service Bulletin 

A320–57–1175, Revision 01, including 

Appendix 01 and Appendix 02, dated 

May 28, 2014. The service information 

describes procedures for repetitive high 

frequency eddy current inspections for 

cracking of the radius of the rib flanges 

and vertical stiffener at frame 36, a 

rototest inspection for cracking of the 

fastener holes of the rib flanges, and 

repair. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests 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 identified 

previously include procedures and tests 

that are identified as RC (required for 

compliance) because these procedures 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests identified as RC 

must be done to comply with the 

proposed AD. However, procedures and 

tests that are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

Although Airbus Service Bulletin 

A320–57–1175, Revision 01, including 

Appendix 01 and Appendix 02, dated 

May 28, 2014, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, this proposed 

AD would require repairing those 

conditions using a method approved by 

the Manager, International Branch, 

ANM–116, Transport Airplane 

Directorate, FAA; or EASA or its 

delegated agent, or Airbus’ EASA 

Design Organization Approval (DOA). 

Costs of Compliance 

We estimate that this proposed AD 

affects 11 airplanes of U.S. registry. 

The actions required by AD 97–07–14, 

Amendment 39–9988 (62 FR 16473, 

April 7, 1997), and retained in this 

proposed AD take about 13 work-hours 

per product, at an average labor rate of 

$85 per work-hour. Required parts cost 

about $576 per product. Based on these 

figures, the estimated cost of the actions 

that are required by AD 97–07–14 is 

$1,681 per product. 

We also estimate that it would take 

about 45 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $1,600 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $59,675, or $5,425 

per product. 

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: 


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Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules 22945 

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 

removing Airworthiness Directive (AD) 

97–07–14, Amendment 39–9988 (62 FR 

16473, April 7, 1997), and adding the 

following new AD: 

Airbus: Docket No. FAA–2015–0926; 

Directorate Identifier 2014–NM–121–AD. 

(a) Comments Due Date 

We must receive comments by June 8, 

2015. 

(b) Affected ADs 

This AD replaces AD 97–07–14, 

Amendment 39–9988 (62 FR 16473, April 7, 

1997). 

(c) Applicability 

This AD applies to Airbus Model A320– 

211 and –231 airplanes, certificated in any 

category, all manufacturer serial numbers 

(MSN) up to MSN 0084 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by the 

determination that repetitive inspections are 

needed on airplanes on which the 

modification of the rib flange on the front 

spar of the wing center section has been 

done. We are issuing this AD to prevent 

fatigue cracking on the rib flange area of the 

front spar of the wing center section, which 

can reduce the structural integrity of fuselage 

frame 36 and the wing center section. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification 

This paragraph restates the requirements of 

paragraph (a) of AD 97–07–14, Amendment 

39–9988 (62 FR 16473, April 7, 1997). For 

airplanes with manufacturer serial number 

(MSN) 005 through 008 inclusive, MSN 010 

through 014 inclusive, and MSN 016 through 

042 inclusive: Prior to the accumulation of 

16,000 total landings, or within 3 months 

after May 12, 1997 (the effective date of AD 

97–07–14), whichever occurs later, modify 

the rib flange on the front spar of the wing 

center section by installing shims and new 

fasteners to reinforce pressure floor fittings, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1013, Revision 1, dated September 29, 

1992. 

(h) Modification for Airplanes With MSNs 

001, 009, and 015 

Prior to the accumulation of 16,000 total 

landings since first flight, or within 30 days 

after the effective date of this AD, whichever 

occurs later, modify the rib flange on the 

front spar of the wing center section by 

installing shims and new fasteners to 

reinforce pressure floor fittings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1013, Revision 1, dated September 29, 

1992. 

(i) New Requirement of This AD: Repetitive 

Inspections 

Within the applicable compliance times 

specified in paragraphs (i)(1) and (i)(2) of this 

AD, do a high frequency eddy current (HFEC) 

inspection for cracking of the radius of the 

rib flanges and vertical stiffener at frame 36 

and do a rototest inspection for cracking of 

the fastener holes of the rib flanges and 

vertical stiffener, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1175, Revision 01, 

including Appendix 01, dated May 28, 2014. 

During each inspection, remove the shims 

and fasteners on the rib flange on the front 

spar side and do an HFEC inspection for 

cracking of the radius of the rib flanges and 

a rototest inspection for cracking of the 

fastener holes. If no cracking is found, 

oversize the holes of the rib flange and the 

holes of the shims, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1175, Revision 01, 

including Appendix 01, dated May 28, 2014. 

Repeat the inspections thereafter at intervals 

not to exceed 32,500 flight cycles or 65,000 

flight hours, whichever occurs first. 

(1) For airplanes having Airbus 

Modification 20976 embodied: At the later of 

the times specified in paragraphs (i)(1)(i) or 

(i)(1)(ii) of this AD. 

(i) Before exceeding 47,800 flight cycles or 

95,600 flight hours, whichever occurs first, 

since the airplane’s first flight. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(2) For airplanes on which the 

modification of the front spar of the wing 

center section was accomplished using 

Airbus Service Bulletin A320–57–1013, 

Revision 1, dated September 29, 1992: At the 

later of the times specified in paragraphs 

(i)(2)(i) or (i)(2)(ii) of this AD. 

(i) Before exceeding 10,700 flight cycles or 

21,500 flight hours, whichever occurs first, 

after the modification of the rib flange on the 

front spar of the wing center section was 

done using Airbus Service Bulletin A320– 

57–1013, Revision 1, dated September 29, 

1992. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(j) Repair 

If, during any inspection required by 

paragraph (i) of this AD, any cracking is 

found, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(k) Credit for Previous Actions 

This paragraph restates the requirements of 

Note 2 of paragraph (g) of AD 97–07–14, 

Amendment 39–9988 (62 FR 16473, April 7, 

1997): This paragraph provides credit for the 

modification of the rib flange required by 

paragraph (g) of this AD, if those actions were 

performed before May 12, 1997 (the effective 

date of AD 97–07–14) using Airbus Service 

Bulletin A320–57–1013, dated April 12, 

1989. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 


tkelley on DSK3SPTVN1PROD with PROPOSALS
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Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (j) of this AD, if the 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and tests that 

are not identified as RC are recommended. 

Those procedures and tests that are not 

identified 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 procedures and tests 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to procedures 

or tests identified as RC require approval of 

an AMOC. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0053, dated 

March 7, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2015–0926. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

You may view this 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 April 6, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–09549 Filed 4–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–0046; Airspace 

Docket No. 14–ASO–23] 

Proposed Establishment of Class E 

Airspace; Headland, AL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish Class E Airspace at Headland, 

AL, to accommodate new Area 

Navigation (RNAV) Global Positioning 

System (GPS) Standard Instrument 

Approach Procedures (SIAPs) serving 

Headland Municipal Airport. Controlled 

airspace is necessary for the safety and 

management of instrument flight rules 

(IFR) operations at the airport. 

DATES: 0901 UTC. Comments must be 

received on or before June 8, 2015. 

ADDRESSES: Send comments on this rule 

to: U. S. Department of Transportation, 

Docket Operations, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey, SE., Washington, DC 

20590–0001; Telephone: 1–800–647– 

5527; Fax: 202–493–2251. You must 

identify the Docket Number FAA–2015– 

0046; Airspace Docket No. 14–ASO–23, 

at the beginning of your comments. You 

may also submit and review received 

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 proposed 

incorporation by reference 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: John 

Fornito, Operations Support Group, 

Eastern Service Center, Federal Aviation 

Administration, P.O. Box 20636, 

Atlanta, Georgia 30320; telephone (404) 

305–6364. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

comment on this rule 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– 

2015–0046; Airspace Docket No. 14– 

ASO–23) 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. 

Persons 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 

Docket No. FAA–2015–0046; Airspace 

Docket No. 14–ASO–23.’’ The postcard 

will be date/time stamped and returned 

to the commenter. 

All communications received before 

the specified closing date for comments 

will be considered before taking action 

on the proposed rule. The proposal 

contained in this notice may be changed 

in light of the comments received. A 

report summarizing each substantive 

public contact with FAA personnel 

concerned with this rulemaking will be 

filed in the docket. 

Availability of NPRMs 

An electronic copy of this document 

may be downloaded from and 


tkelley on DSK3SPTVN1PROD with PROPOSALS