74058 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 

searching for and locating Docket No. FAA– 

2015–5813. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.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 

November 17, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30022 Filed 11–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5811; Directorate 

Identifier 2014–NM–158–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) 2004–19– 

11 for certain Airbus Model 320 series 

airplanes. AD 2004–19–11 currently 

requires modification of the inner rear 

spar web of the wing, cold expansion of 

the attachment holes of the forward 

pintle fitting and the actuating cylinder 

anchorage of the main landing gear 

(MLG), repetitive ultrasonic inspections 

for cracking of the rear spar of the wing, 

and corrective action if necessary. AD 

2004–19–11 also provides optional 

terminating action for the repetitive 

inspections. Since we issued AD 2004– 

19–11, we have determined that the 

terminating action is necessary to 

address the unsafe condition. This 

proposed AD is intended to complete 

certain mandated programs intended to 

support the airplane reaching its limit of 

validity (LOV) of the engineering data 

that support the established structural 

maintenance program. This proposed 

AD would retain the requirements of AD 

2004–19–11 and would require the 

previously optional terminating action. 

We are proposing this AD to prevent 

fatigue cracking of the inner rear spar, 

which may lead to reduced structural 

integrity of the wing and the MLG. 

DATES: We must receive comments on 

this proposed AD by January 11, 2016. 

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– 

5811; 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 ADDRESSESsection. 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–2015–5811; Directorate Identifier 

2014–NM–158–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 September 21, 2004, we issued AD 

2004–19–11, Amendment 39–13805 (69 

FR 58828, October 1, 2004). AD 2004– 

19–11 requires actions intended to 

address an unsafe condition on certain 

Airbus Model 320 series airplanes. AD 

2004–19–11 superseded AD 2000–10– 

15, Amendment 39–17739 (65 FR 

34069, May 26, 2000). 

Since we issued AD 2004–19–11, 

Amendment 39–13805 (69 FR 58828, 

October 1, 2004), we have determined 

that the modification of the inner rear 

spar that is an optional terminating 

action of AD 2004–19–11 must be 

accomplished in order to address the 

identified unsafe condition. 

As described in FAA Advisory 

Circular 120–104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120–104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a limit of validity (LOV) of the 

engineering data that support the 

structural maintenance program under 

14 CFR 26.21. This proposed AD is the 

result of an assessment of the previously 

established programs by the design 

approval holder (DAH). The actions 

specified in this proposed AD are 

necessary to complete certain programs 

to ensure the continued airworthiness of 

aging airplane structure and to support 

an airplane reaching its LOV. 

The European Aviation Safety 

Agency, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0169, corrected July 22, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain Airbus 

Model A320 series airplanes. The MCAI 

states: 

During centre fuselage certification full 

scale fatigue test, cracks were found on the 

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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74059 

inner rear spar at holes position 52 on the 

right hand wing due to fatigue aspects. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To prevent such cracks, Airbus developed 

modifications, which were introduced in 

production and in service through several 

Airbus Service Bulletins (SB). DGAC France 

issued * * * [an earlier AD], which was 

subsequently superseded by [DGAC] AD 

2001–249 [which corresponds with FAA AD 

2004–19–11, Amendment 39–13805 (69 FR 

58828, October 1, 2004)], to require 

modification of the rear spar on some 

aeroplanes, post-modification repetitive 

inspections and, depending on findings, 

accomplishment of a repair. DGAC France 

AD 2001–249 also specified that modification 

in accordance with Airbus SB A320–57–1089 

(in-service equivalent to Airbus mod 24591) 

constituted (optional) terminating action for 

the repetitive inspections. 

Since that [DGAC] AD [2001–249] was 

issued, in the framework of the A320 

Extended Service Goal (ESG), it has been 

determined that Airbus mod 24591 is 

necessary to allow aeroplanes to operate up 

to the new ESG limit. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France AD 2001–249, which is superseded, 

and requires modification of all pre-mod 

24591 aeroplanes. 

The modification includes modifying 

all specified fastener holes in the inner 

rear spar of the wing. 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–2015–5811. 

Related Service Information Under 1 

CFR part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A320–57– 

1004, Revision 02, dated June 14, 1993. 

This service information describes 

procedures for modifying the inner rear 

spar web of the wing. 

• Airbus Service Bulletin A320–57– 

1060, Revision 2, dated December 16, 

1994. This service information describes 

procedures for a cold expansion of all 

the attachment holes for the forward 

pintle fitting of the main landing gear 

(MLG), except for the holes that are for 

taper-lok bolts; and for a cold expansion 

of the holes at the actuating cylinder 

anchorage of the MLG. 

• Airbus Mandatory Service Bulletin 

A320–57–1088, Revision 04, dated 

August 6, 2001. This service 

information describes procedures for 

doing ultrasonic inspections for 

cracking of the rear spar of the wing. 

• Airbus Service Bulletin A320–57– 

1089, Revision 03, dated February 9, 

2001. This service information describes 

modification of the airplane by 

accomplishing cold reexpansion of the 

holes in the inner rear spar for the 

attachment of gear rib 5, forward pintle 

fitting, and actuating cylinder 

anchorage; and the installation of 

interference fit fasteners in the rear spar 

and gear rib 5. 

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 ADDRESSESsection of 

this NPRM. 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 84 airplanes of U.S. registry. 

The actions required by AD 2004–19– 

11, Amendment 39–13805 (69 FR 

58828, October 1, 2004), and retained in 

this proposed AD take about 684 workhours per product, at an average labor 

rate of $85 per work-hour. Required 

parts cost about $13,644 per product. 

Based on these figures, the estimated 

cost of the actions that are required by 

AD 2004–19–11 is $71,784 per product. 

We also estimate that it would take 

about 980 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 $32,727 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $9,746,268, or 

$116,027 per product. 

We 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 

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) 

2004–19–11, Amendment 39–13805 (69 

FR 58828, October 1, 2004), and adding 

the following new AD: 

Airbus: Docket No. FAA–2015–5811; 

Directorate Identifier 2014–NM–158–AD. 

(a) Comments Due Date 

We must receive comments by 

January 11, 2016. 

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74060 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 

(b) Affected ADs 

This AD replaces AD 2004–19–11, 

Amendment 39–13805 (69 FR 58828, 

October 1, 2014). 

(c) Applicability 

This AD applies to Airbus Model 

A320–211, –212, –214, –231, –232, and 

–233 airplanes, certificated in any 

category, all manufacturer serial 

numbers, except those on which Airbus 

modification (mod) 24591 has been 

embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

fatigue cracking of the inner rear spar of 

the wing and also by the determination 

that the modification of the inner rear 

spar is necessary to address the unsafe 

condition. We are issuing this AD to 

prevent fatigue cracking of the inner 

rear spar, which may lead to reduced 

structural integrity of the wing and the 

main landing gear (MLG). 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless 

already done. 

(g) Retained Modification of Inner Rear 

Spar Web of the Wing, With Change to 

Acceptable Service Information 

This paragraph restates the 

requirements of paragraph (a) of AD 

2004–19–11, Amendment 39–13805 (69 

FR 58828, October 1, 2004), with a 

change to acceptable service 

information. For airplanes having 

manufacturer’s serial numbers (MSNs) 

003 through 008 inclusive, and 010 

through 021 inclusive, except airplanes 

modified as specified in Airbus Service 

Bulletin A320–57–1089, dated 

December 22, 1996; Revision 01, dated 

April 17, 1997; Revision 02, dated 

November 6, 1998; or Revision 03, dated 

February 9, 2001: Prior to the 

accumulation of 12,000 total flight 

cycles, or within 500 flight cycles after 

June 11, 1993 (the effective date of AD 

93–08–15, Amendment 39–8563 (58 FR 

27923, May 12, 1993)), whichever 

occurs later, modify the inner rear spar 

web of the wing in accordance with 

Airbus Service Bulletin A320–57–1004, 

Revision 1, dated September 24, 1992; 

or Revision 2, dated June 14, 1993. As 

of the effective date of this AD, only 

Airbus Service Bulletin A320–57–1004, 

Revision 2, dated June 14, 1993, may be 

used for the actions required by this 

paragraph. 

(h) Retained Cold Expansion of Holes at 

Forward Pintle Fitting and Actuating 

Cylinder Anchorage of the Main 

Landing Gear, With Change to 

Acceptable Service Information 

This paragraph restates the 

requirements of paragraph (b) of AD 

2004–19–11, Amendment 39–13805 (69 

FR 58828, October 1, 2004), with a 

change to acceptable service 

information. For airplanes having MSNs 

002 through 051 inclusive, except 

airplanes modified as specified in 

Airbus Service Bulletin A320–57–1089, 

dated December 22, 1996; Revision 01, 

dated April 17, 1997; Revision 02, dated 

November 6, 1998; or Revision 03, dated 

February 9, 2001: Prior to the 

accumulation of 12,000 total flight 

cycles, or within 2,000 flight cycles after 

February 14, 1994 (the effective date of 

AD 93–25–13, Amendment 39–8777 (59 

FR 1903, January 13, 1994)), whichever 

occurs later, accomplish the 

requirements of paragraphs (h)(1) and 

(h)(2) of this AD in accordance with 

Airbus Service Bulletin A320–57–1060, 

dated December 8, 1992; Revision 1, 

dated April 26, 1993; or Revision 2, 

dated December 16, 1994. As of the 

effective date of this AD, only Airbus 

Service Bulletin A320–57–1060, 

Revision 2, dated December 16, 1994, 

may be used for the actions required by 

this paragraph. 

(1) Perform a cold expansion of all the 

attachment holes for the forward pintle 

fitting of the main landing gear (MLG), 

except for the holes that are for taperlok bolts. 

(2) Perform a cold expansion of the 

holes at the actuating cylinder 

anchorage of the MLG. 

(i) Retained Repetitive Ultrasonic 

Inspections for Cracking of the Rear 

Spar of the Wing, With No Changes 

This paragraph restates the 

requirements of paragraphs (c), (d), and 

(e) of AD 2004–19–11, Amendment 39– 

13805 (69 FR 58828, October 1, 2004), 

with no changes. Except for airplanes 

modified as specified in Airbus Service 

Bulletin A320–57–1089, dated 

December 22, 1996; Revision 01, dated 

April 17, 1997; Revision 02, dated 

November 6, 1998; or Revision 03, dated 

February 9, 2001: Do the actions 

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

of this AD. 

(1) Do an ultrasonic inspection for 

cracking of the rear spar of the wing, in 

accordance with Airbus Service Bulletin 

A320–57–1088, Revision 04, dated 

August 6, 2001. Inspect at the applicable 

time specified in paragraph 1.E. of 

Airbus Service Bulletin A320–57–1088, 

Revision 04, dated August 6, 2001, 

except as required by paragraphs (i)(1)(i) 

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

(i) For any airplane that has not been 

inspected but has exceeded the 

applicable specified compliance time in 

paragraph 1.E. of Airbus Service 

Bulletin A320–57–1088, Revision 04, 

dated August 6, 2001, as of November 

5, 2004 (the effective date of AD 2004– 

19–11, Amendment 39–13805 (69 FR 

58828, October 1, 2004)): Inspect within 

18 months after November 5, 2004. 

(ii) For any airplane that has been 

inspected before November 5, 2004 (the 

effective date of AD 2004–19–11, 

Amendment 39–13805 (69 FR 58828, 

October 1, 2004): Repeat the inspection 

within 3,600 flight cycles after the most 

recent inspection. 

(2) Repeat the inspection required by 

paragraph (i)(1) of this AD at intervals 

not to exceed 3,600 flight cycles or 

6,700 flight hours, whichever occurs 

first, until the requirements of 

paragraph (k) of this AD have been 

done. 

(j) Retained Corrective Action for 

Inspections Required by Paragraphs 

(i)(1) and (i)(2) of This AD, With 

Specific Delegation Approval Language. 

This paragraph restates the 

requirements of paragraph (f) of AD 

2004–19–11, Amendment 39–13805 (69 

FR 58828, October 1, 2004), with 

specific delegation approval language. If 

any crack is found during any 

inspection required by paragraph (i)(1) 

or (i)(2) of this AD: Before further flight, 

repair in accordance with a method 

approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(or its delegated agent); or the European 

Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). Accomplishment of a 

repair as required by this paragraph 

does not constitute terminating action 

for the repetitive inspections required 

by paragraph (i)(2) of this AD. 

(k) New Requirement of This AD: 

Modification of Inner Rear Spar 

Before exceeding 48,000 flight cycles 

or 96,000 flight hours, whichever occurs 

first since first flight of the airplane: 

modify all specified fastener holes in 

the inner rear spar of the wing, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin 

A320–57–1089, Revision 03, dated 

February 9, 2001; except where Airbus 

Service Bulletin A320–57–1089, 

Revision 03, dated February 9, 2001, 

specifies to contact Airbus for certain 

conditions, before further flight, repair 

using a method approved by the 

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Manager, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA; or EASA; or Airbus’s EASA DOA. 

Modification of all specified fastener 

holes in the rear spar of the wing 

terminates the initial and repetitive 

inspections required by paragraphs (i)(1) 

and (i)(2) of this AD. If the modification 

is done both before the airplane 

accumulates 12,000 total flight cycles 

and before the effective date of this AD, 

the modification also terminates the 

actions required by paragraphs (g) and 

(h) of this AD. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (i) of this 

AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–57–1088, 

Revision 02, dated July 29, 1999; or 

Revision 03, dated February 9, 2001, 

which are not incorporated by reference 

in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (k) of this 

AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–57–1089, 

Revision 02, dated November 6, 1998, 

which is not incorporated by reference 

in this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

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. 

(i) 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. 

(ii) AMOCs approved previously in 

accordance with AD 2004–19–11, 

Amendment 39–13805 (69 FR 58828, October 

1, 2004), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

through (j) of 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 

the European Aviation Safety Agency 

(EASA); or Airbus’ EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0169, 

corrected July 22, 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–2015–5811. 

(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 

November 17, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30006 Filed 11–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–4452; Airspace 

Docket No. 15–AWA–7] 

RIN 2120–AA66 

Proposed Amendment of Class C 

Airspace; Capital Region International 

Airport, MI 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

modify Class C airspace at Capital 

Region International Airport, formerly 

Lansing Capital City Airport, Lansing, 

MI, by removing a cutout from the 

surface area that was put in place to 

accommodate operations around Davis 

Airport, now permanently closed. Also, 

this proposal would update the airport’s 

name and geographic coordinates to 

reflect the current information in the 

FAA’s aeronautical database. The FAA 

is proposing this action to enable more 

efficient operations at Capital Region 

International Airport. 

DATES: Comments must be received on 

or before January 26, 2016. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, M– 

30, 1200 New Jersey Avenue SE., West 

Building Ground Floor, Room W12–140, 

Washington, DC 20590–0001; telephone: 

(202) 366–9826. You must identify FAA 

Docket No. FAA–2015–4452 and 

Airspace Docket No. 15–AWA–7 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 7400.9Z, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

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

publications/. For further information, 

you can contact the Airspace Policy 

Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC, 20591; 

telephone: (202) 267–8783. 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_federalregulations/ibr_locations.html. 

FAA Order 7400.9, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. 

FOR FURTHER INFORMATION CONTACT: 

Colby Abbott, Airspace Policy Group, 

Office of Airspace Services, Federal 

Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone: (202) 

267–8783. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. 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 

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