This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

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REGISTER issue of each week.

Rules and Regulations Federal Register

78899 

Vol. 81, No. 218 

Thursday, November 10, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3985; Directorate 

Identifier 2014–NM–182–AD; Amendment 

39–18708; AD 2016–23–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2010–04– 

03 for all Airbus Model A310 series 

airplanes. AD 2010–04–03 required 

accomplishing repetitive detailed 

inspections for cracking around the 

fastener holes in certain wing top skin 

panels between the front and rear spars 

on the left- and right-hand sides of the 

fuselage, and repair if necessary. This 

new AD continues to require the 

repetitive detailed inspections, and also 

requires supplemental repetitive 

ultrasonic inspections for cracking 

around the fastener holes in wing top 

skin panels 1 and 2 at ribs 2 and 3, and 

repair if necessary. This AD was 

prompted by development of an 

ultrasonic inspection program to allow 

for earlier crack detection and extended 

repetitive inspection intervals. We are 

issuing this AD to detect and correct 

fatigue cracking around the fastener 

holes, which could result in reduced 

structural integrity of the airplane. 

DATES: This AD is effective December 

15, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 15, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2015–3985. 

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– 

3985; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to supersede AD 

2010–04–03, Amendment 39–16196 (75 

FR 6852, February 12, 2010) (‘‘AD 2010– 

04–03’’). AD 2010–04–03 applied to all 

Airbus Model A310 series airplanes. 

The SNPRM published in the Federal 

Register on July 11, 2016 (81 FR 44812) 

(‘‘the SNPRM’’). We preceded the 

SNPRM with a notice of proposed 

rulemaking (NPRM) that published in 

the Federal Register on October 13, 

2015 (80 FR 61327) (‘‘the NPRM’’). The 

NPRM was prompted by development of 

an ultrasonic inspection program to 

allow for earlier crack detection and 

extended repetitive inspection intervals. 

The NPRM proposed to retain the 

requirements of AD 2010–04–03, and 

proposed to require supplemental 

repetitive ultrasonic inspections for 

cracking around the fastener holes in 

wing top skin panels 1 and 2 at rib 2, 

and repair if necessary. The SNPRM 

proposed to expand the inspection area 

to include rib 3 due to widespread 

fatigue damage. We are issuing this AD 

to detect and correct fatigue cracking 

around the fastener holes, which could 

result in reduced structural integrity of 

the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2016–0005, dated January 7, 

2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Airbus Model 

A310 series airplanes. The MCAI states: 

Following scheduled maintenance, cracks 

were found around the wing top skin panels 

fastener holes at Rib 2, between Stringer 

(STG) 2 and STG14. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. The General Visual 

Inspection required by the existing 

applicable Airworthiness Limitation Items 

(ALI) tasks may not be adequate to detect 

these cracks. 

To address this issue, Airbus developed an 

inspection programme based on repetitive 

detailed inspections (DET) to ensure that any 

visible cracks in the wing top skin panels 1 

and 2 along Rib 2 are detected in time and 

repaired appropriately. EASA issued AD 

2008–0211 to require implementation of this 

inspection programme. 

After that [EASA] AD was issued, Airbus 

improved the inspection programme with an 

ultrasonic inspection to allow earlier crack 

detection, to subsequently reduce the scope 

of potential repair action, and to extend the 

intervals of the repetitive inspections. 

Consequently, EASA issued AD 2014–0200 

(later revised), superseding [EASA] AD 2008– 

0211, retaining its requirements, and to 

require supplementary repetitive ultrasonic 

inspections [for cracking] of the wing top 

skin panel 1 and 2 between STG2 and STG10 

at Rib 2 [and repair if needed]. 

Since EASA AD 2014–0020R1 was issued, 

a widespread fatigue damage analysis 

concluded that the inspection programme 

has to be extended to include the wing top 

skin panels at Rib 3 attachments. For the 

reasons described above, this [EASA] AD 


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retains the requirements of EASA AD 2014– 

0200R1, which is superseded, and extends 

the inspection area to include Rib 3. 

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– 

3985. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM or 

on the determination of the cost to the 

public. 

Clarification of Requirements 

We have clarified the terminating 

action sentence in paragraph (k) of this 

AD by adding a reference to paragraph 

(g) of this AD. 

We have clarified the average flight 

time in paragraph (l)(3) of this AD for 

subsequent inspections after the second 

inspection interval. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR part 51 

Airbus has issued Service Bulletin 

A310–57–2096, Revision 03, dated June 

30, 2015. This service information 

describes procedures for detailed and 

ultrasonic inspections for cracking 

around the fastener holes of wing top 

skin panels 1 and 2, at ribs 2 and 3, on 

the left- and right-hand sides of the 

fuselage. 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. 

Costs of Compliance 

We estimate that this AD affects 28 

airplanes of U.S. registry. 

We also estimate that it takes about 8 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$19,040, or $680 per product. 

We estimate that it takes about 15 

work-hours per product to do any 

necessary on-condition actions that are 

required based on the results of the 

inspections. Required parts will cost 

about $10,000 per product. We have no 

way of determining the number of 

aircraft that might need these actions. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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) 

2010–04–03, Amendment 39–16196 (75 

FR 6852, February 12, 2010), and adding 

the following new AD: 

2016–23–01 Airbus: Amendment 39–18708; 

Docket No. FAA–2015–3985; Directorate 

Identifier 2014–NM–182–AD. 

(a) Effective Date 

This AD is effective December 15, 2016. 

(b) Affected ADs 

This AD replaces AD 2010–04–03, 

Amendment 39–16196 (75 FR 6852, February 

12, 2010) (‘‘AD 2010–04–03’’). 

(c) Applicability 

This AD applies to all Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by the 

development of an ultrasonic inspection 

program to allow for earlier crack detection 

and extended repetitive inspection intervals. 

We are issuing this AD to detect and correct 

fatigue cracking around the fastener holes in 

certain wing top skin panels between the 

front and rear spars on the left- and righthand sides of the fuselage, which could 

result in reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Except as required by paragraph (i) of this 

AD: Within the initial compliance time and 

thereafter at the repetitive intervals specified 

in paragraphs (h)(1) through (h)(3) of this AD, 

as applicable, accomplish the actions 

specified in paragraphs (g)(1) and (g)(2) of 

this AD concurrently and in sequence, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2096, Revision 03, dated June 30, 2015, 

except as provided by paragraph (j) of this 

AD. 

(1) Accomplish a detailed inspection for 

cracking around the fastener holes in the 

wing top skin panels 1 and 2, along ribs 2 

and 3, between the front and rear spars on 

the left- and right-hand sides of the fuselage. 

(2) Accomplish an ultrasonic inspection for 

cracking around the fastener holes in the 

wing top skin panels 1 and 2, along ribs 2 

and 3, between stringer (STG) 2 and STG10 


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on the left- and right-hand sides of the 

fuselage. 

(h) Compliance Times for Airplanes Not 

Previously Inspected 

(1) For Model A310–203, –204, –221, and 

–222 airplanes: Do the actions required by 

paragraphs (g)(1) and (g)(2) of this AD at the 

later of the times specified in paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD. Repeat the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD thereafter at intervals not to 

exceed 2,000 flight cycles or 4,100 flight 

hours, whichever occurs first. 

(i) Prior to the accumulation of 18,700 

flight cycles or 37,400 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(2) For Model A310–304, –322, –324, and 

–325 airplanes having an average flight time 

(AFT) of less than 4 hours: Do the actions 

required by paragraphs (g)(1) and (g)(2) of 

this AD at the later of the times specified in 

paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. 

Repeat the inspections specified in 

paragraphs (g)(1) and (g)(2) of this AD 

thereafter at intervals not to exceed 2,000 

flight cycles or 5,600 flight hours, whichever 

occurs first. 

(i) Prior to the accumulation of 17,300 

flight cycles or 48,400 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(3) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of equal to or 

more than 4 hours: Do the actions required 

by paragraphs (g)(1) and (g)(2) of this AD at 

the later of the times specified in paragraphs 

(h)(3)(i) and (h)(3)(ii) of this AD. Repeat the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD thereafter at intervals not to 

exceed 1,500 flight cycles or 7,500 flight 

hours, whichever occurs first. 

(i) Prior to the accumulation of 12,800 

flight cycles or 64,300 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(i) Compliance Times for Airplanes 

Previously Inspected 

For airplanes previously inspected before 

the effective date of this AD using Airbus 

Service Bulletin A310–57–2096, dated May 

6, 2008; Airbus Service Bulletin A310–57– 

2096, Revision 01, dated August 5, 2010; or 

Airbus Service Bulletin A310–57–2096, 

Revision 02, dated March 5, 2014: At the 

applicable compliance times specified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD, 

accomplish the actions specified in 

paragraphs (g)(1) and (g)(2) concurrently and 

in sequence, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2096, Revision 03, 

dated June 30, 2015. Repeat the inspections 

specified in paragraphs (g)(1) and (g)(2) of 

this AD thereafter at the repetitive intervals 

specified in paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD, as applicable. 

(1) For Model A310–203, –204, –221, and 

–222 airplanes: Do the actions required by 

paragraphs (g)(1) and (g)(2) of this AD within 

3,500 flight hours or 1,700 flight cycles, 

whichever occurs first since the most recent 

inspection. 

(2) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of less than 4 

hours: Do the actions required by paragraphs 

(g)(1) and (g)(2) of this AD within 4,600 flight 

hours or 1,600 flight cycles, whichever 

occurs first since the most recent inspection. 

(3) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of equal to or 

more than 4 hours: Do the actions required 

by paragraphs (g)(1) and (g)(2) of this AD 

within 6,100 flight hours or 1,200 flight 

cycles, whichever occurs first since the most 

recent inspection. 

(j) Compliance Times if No Ultrasonic 

Equipment is Available 

If no ultrasonic equipment is available for 

the initial or second inspection required by 

paragraph (g) or (h) of this AD, accomplish 

the detailed inspection specified in 

paragraph (g)(1) of this AD within the 

applicable compliance times specified in 

paragraphs (j)(1) and (j)(2) of this AD. After 

accomplishing the detailed inspection, do the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD at the applicable compliance 

times specified by paragraphs (i)(1), (i)(2), 

and (i)(3) of this AD. Subsequently, repeat 

the inspections specified in paragraphs (g)(1) 

and (g)(2) of this AD thereafter at the 

applicable repetitive intervals specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD. 

(1) For airplanes not previously inspected 

before the effective date of this AD using the 

service information identified in paragraph 

(j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do 

the actions required by paragraph (g)(1) of 

this AD within the initial compliance time 

specified by paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD, as applicable. 

(2) For airplanes previously inspected 

before the effective date of this AD using the 

service information identified in paragraph 

(j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do 

the actions required by paragraph (g)(1) of 

this AD within the applicable compliance 

times specified in paragraphs (i)(1), (i)(2), 

and (i)(3) of this AD. 

(i) Airbus Service Bulletin A310–57–2096, 

dated May 6, 2008. 

(ii) Airbus Service Bulletin A310–57–2096, 

Revision 01, dated August 5, 2010. 

(iii) Airbus Service Bulletin A310–57– 

2096, Revision 02, dated March 5, 2014. 

(k) Repair of Cracking 

If any cracking is found during any 

inspection required by paragraph (g), (h), (i), 

or (j) of this AD, before further flight, repair 

the cracking 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). Accomplishing the repair 

specified in this paragraph terminates the 

repetitive inspections required by paragraph 

(g), (h), (i), or (j) of this AD, as applicable, for 

the repaired area only. 

(l) Definition of Average Flight Time (AFT) 

For the purposes of this AD, the AFT 

should be established as specified in 

paragraphs (l)(1), (l)(2), and (l)(3) of this AD 

for the determination of the compliance 

times. 

(1) The inspection threshold is defined as 

the total flight hours accumulated (counted 

from take-off to touch-down), divided by the 

total number of flight cycles accumulated at 

the effective date of this AD. 

(2) The initial inspection interval is 

defined as the total flight hours accumulated 

divided by the total number of flight cycles 

accumulated at the time of the initial 

inspection threshold. 

(3) The second inspection interval is 

defined as the total flight hours accumulated 

divided by the total number of flight cycles 

accumulated between the initial and second 

inspection threshold. For all inspection 

intervals onwards, the average flight time is 

the flight hours divided by the flight cycles 

accumulated between the last two 

inspections. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using the 

applicable service information identified in 

paragraph (m)(1), (m)(2), or (m)(3) of this AD. 

(1) Airbus Service Bulletin A310–57–2096, 

dated May 6, 2008, which was incorporated 

by reference in AD 2010–04–03. 

(2) Airbus Service Bulletin A310–57–2096, 

Revision 01, dated August 5, 2010, which is 

not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A310–57–2096, 

Revision 02, dated March 5, 2014, which is 

not incorporated by reference in this AD. 

(n) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 


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(3) Required for Compliance (RC): Except 

as required by paragraph (k) of this AD, if any 

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 or 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 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0005, dated 

January 7, 2016, 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– 

2015–3985. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(4) and (p)(5) of this AD. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 15, 2016. 

(i) Airbus Service Bulletin A310–57–2096, 

Revision 03, dated June 30, 2015. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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. 

(5) 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. 

(6) You may view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

28, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–26810 Filed 11–9–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2016–6985; Airspace 

Docket No. 16–AGL–16] 

Amendment of Class E Airspace for 

the Following Illinois Towns; Carmi, IL; 

De Kalb, IL; Harrisburg, IL; Kewanee, 

IL; Litchfield, IL; Paris, IL; and 

Taylorville, IL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies Class E 

airspace extending upward from 700 

feet above the surface at Carmi 

Municipal Airport, Carmi, IL; De Kalb 

Taylor Municipal Airport, De Kalb, IL; 

Harrisburg-Raleigh Airport, Harrisburg, 

IL; Kewanne Municipal Airport, 

Kewanne, IL; Litchfield Municipal 

Airport, Litchfield, IL; Edgar County 

Airport, Paris, IL; and Taylorville 

Municipal Airport, Taylorville, IL. 

Decommissioning of non-directional 

radio beacons (NDB), cancellation of 

NDB approaches, or implementation of 

area navigation (RNAV) procedures 

have made this action necessary for the 

safety and management of Instrument 

Flight Rules (IFR) operations at the 

above airports. This action also updates 

the geographic coordinates of Carmi 

Municipal Airport, De Kalb Taylor 

Municipal Airport, Harrisburg-Raleigh 

Airport, Litchfield Municipal Airport, 

Edgar County Airport, and Taylorville 

Municipal Airport to coincide with the 

FAA’s aeronautical database. 

DATES: Effective 0901 UTC, March 2, 

2017. The Director of the Federal 

Register approves this incorporation by 

reference action under Title 1, Code of 

Federal Regulations, part 51, subject to 

the annual revision of FAA Order 

7400.11 and publication of conforming 

amendments. 

ADDRESSES: FAA Order 7400.11A, 

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 FAA 

Order 7400.11A at NARA, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federalregulations/ibr_locations.html. 

FAA Order 7400.11, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Claypool, Federal Aviation 

Administration, Operations Support 

Group, Central Service Center, 10101 

Hillwood Parkway, Fort Worth, TX, 

76177; telephone (817) 222–5711. 

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 

of 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 amends 

Class E airspace at Carmi Municipal 

Airport, Carmi, IL; De Kalb Taylor 

Municipal Airport, De Kalb, IL; 

Harrisburg-Raleigh Airport, Harrisburg, 

IL; Kewanne Municipal Airport, 

Kewanne, IL; Litchfield Municipal 

Airport, Litchfield, IL; Edgar County 

Airport, Paris, IL; and Taylorville 

Municipal Airport, Taylorville, IL. 

History 

On July 1, 2016, the FAA published 

in the Federal Register a notice of 

proposed rulemaking (NPRM), (81 FR 

43124) Docket No. FAA–2016–6985, to 

modify Class E airspace at Carmi 

Municipal Airport, Carmi, IL; De Kalb 

Taylor Municipal Airport, De Kalb, IL; 

Harrisburg-Raleigh Airport, Harrisburg, 

IL; Kewanne Municipal Airport, 

Kewanne, IL; Litchfield Municipal 

Airport, Litchfield, IL; Edgar County 

Airport, Paris, IL; and Taylorville 

Municipal Airport, Taylorville, IL. 

Interested parties were invited to 

participate in this rulemaking effort by 

submitting written comments on the 

proposal to the FAA. No comments 

were received. The FAA discovered a 

typographical error in the geographic 

coordinate of Harrisburg-Raleigh Airport 

which has been corrected in this action. 

Class E airspace designations are 

published in paragraph 6005 of FAA 

Order 7400.11A, dated August 3, 2016, 

and effective September 15, 2016, which 


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