## 34876 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations

Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015: Except as required by paragraph (t)(1) of this AD, at the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015, do HFEC, LFEC, and detailed inspections for cracking in accordance with ‘‘Part 7—INSPECTION OF PREVENTATIVE MODIFICATION’’ of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable interval specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this
AD.
(r) New Requirement of This AD: Inspections of Preventive Modification for Groups 1–6, Configuration 2, Airplanes

For airplanes identified as Groups 1 through 6, Configuration 2, in Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015: Except as required by paragraph (t)(1) of this AD, at the applicable time specified in table 4 or table 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015, do HFEC, LFEC, and detailed inspections for cracking in accordance with ‘‘Part 8—INSPECTION OF PREVENTATIVE MODIFICATION’’ of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable interval specified in table 4 or table 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this
AD.
(s) New Requirement of This AD: Inspections of Preventive Modification for Groups 4–6, Configuration 1, Airplanes

For airplanes identified as Groups 4 through 6, Configuration 1, in Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015: At the applicable time specified in table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015, except as required by paragraph (t)(1) of this AD: Do HFEC and detailed inspections for cracking in accordance with ‘‘Part 7—INSPECTION OF PREVENTATIVE MODIFICATION’’ of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD.
(t) New Requirement of This AD: Exceptions to Service Bulletin Specifications

(1) Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015, refers to a compliance time ‘‘after the Revision 2 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

(2) The ‘‘Condition’’ column in table 1 and table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1279, Revision 2, dated April 21, 2015, refers to total flight cycles ‘‘at the Revision 2 date of this service bulletin.’’ However, this AD applies to the airplanes with the specified total flight cycles as of the effective date of this AD.
(u) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Los Angeles 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 (v)(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, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes ODA that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD.

(4) AMOCs approved for the ADs in paragraphs (u)(4)(i) through (u)(4)(iii) of this AD are approved as AMOCs for the corresponding provisions of this AD.

(i) AD 2009–02–06, Amendment 39–15796 (74 FR 10469, March 11, 2009).

(ii) AD 2009–02–06 R1, Amendment 39– 16015 (74 FR 45979, September 8, 2009).

(iii) AD 2011–23–05.

(v) Related Information

(1) For more information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5324; fax: 562–627–5210; email: galib.abumeri@faa.gov.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (w)(5) and (w)(6) of this AD. (w) 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 the AD specifies otherwise.

(3) The following service information was approved for IBR on July 6, 2016.

(i) Boeing Alert Service Bulletin 737– 53A1279, Revision 2, dated April 21, 2015.

(ii) Reserved. (4) The following service information was approved for IBR on November 16, 2011 (76 FR 67343, November 1, 2011).

(i) Boeing Alert Service Bulletin 737– 53A1279, Revision 1, dated September 2,
2011.

(ii) Reserved. (5) For Boeing 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.

(6) 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.

(7) 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 May 18,

2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–12329 Filed 5–31–16; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–8465; Directorate Identifier 2014–NM–239–AD; Amendment**  **39–18535; AD 2016–11–08]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Defense and Space S.A. (Formerly Known as Construcciones**  **Aeronauticas, S.A.)**

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding Airworthiness Directive (AD) 2001–12–


## 34877 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations

18 for certain CASA Model CN–235 series airplanes. AD 2001–12–18 required modification of the rigging of the engine control cable assembly and replacement of either the entire engine control cable assembly or a segment of the control cables. This new AD would retain the requirements of AD 2001–12– 18. This new AD also requires repetitive replacements of each power lever and condition lever Teleflex cable with a new or serviceable part, and removes airplanes from the applicability. This AD was prompted by reports of new occurrences of cable disruption on a certain part number; the disruption is caused by microcracks along the cable surface. We are issuing this AD to prevent fatigue of the engine control cables, leading to breakage of the cables, which could result in reduced controllability of the airplane.

**DATES** 

### : This AD is effective July 6, 2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 6, 2016.

The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of July 25, 2001 (66 FR 33014, June 20, 2001).

**ADDRESSES** 

### : For service information identified in this final rule, contact EADS–CASA, Military Transport Aircraft Division (MTAD), Integrated Customer Services (ICS), Technical Services, Avenida de Arago  ́ n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 05; email MTA. TechnicalService@casa.eads.net; Internet http://www.eads.net. 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–

8465. 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– 8465; 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** 

### : Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227– 1112; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001) (‘‘AD 2001–12–18’’). AD 2001–12–18 applied to certain CASA Model CN–235 series airplanes. The NPRM published in the Federal Register on January 19, 2016 (81 FR 2783) (‘‘the NPRM’’).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0262, dated December 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Defense and Space S.A. Model CN–235– 100 and -200 airplanes. The MCAI

states:

Three occurrences of cable disruption were reported in 1999. The failed parts, having a part number (P/N) 7–44728–20, were part of the engine control system assembly P/N 7–44728–12. Two cables were connected to the Power Lever and one cable to the Condition Lever control. Service records of the affected parts showed that each cable accumulated more than 14,000 flight cycles (FC).

The subsequent investigation determined that the disruption was attributed to fatigue related crack.

This condition, if not corrected, could lead to failure of the engine control system resulting in a loss of the affected engine control.

Prompted by this unsafe condition, DGAC [Direccio  ́ n General de Aviacio  ́ n Civil] Spain issued AD 03/00 [which corresponds to FAA AD 2001–12–18] to require rigging of the throttle stops, and one-time replacement of the affected engine control cable assembly (P/N 7–44728–12), or the affected cable (P/N 7–44728–20) before exceeding 12,000 FC.

After that [DGAC Spain] AD was issued, a new occurrence of cable (P/N 72830–20) disruption was reported. In that case, the affected cable was part of the Condition Lever control and had accumulated 8,497 flight hours (FH) and 8,858 FC. Fractographic analysis of the affected cable identified that the fatigue nucleation seemed to have been induced by microcracks along the cable surface. Additionally, another case of control cable (P/N 72830–20) failure was reported, where the affected part accumulated 9,936 FH and 10,552 FC and was part of the Power Lever control. Investigation of the latter case identified again a fatigue nucleation to be the cause of the cable failure.

To address this potentially unsafe condition, Airbus Military issued Alert Operators Transmission (AOT) AOT–CN235– 76–0001 to provide a repetitive replacement interval and instructions.

For the reasons described above, this [EASA] AD retains the requirements of DGAC Spain AD No. 03/00, which is superseded, but requires repetitive replacement [at reduced thresholds] of the affected Teleflex cables. 

### 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–

8465.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.
Clarification of Applicability

We have clarified the Applicability in paragraph (c) of this AD. For Model CN– 235 airplanes, the affected serial numbers (S/N) are C–001 through C–015 inclusive. We have removed S/N C–074 for Model CN–235 airplanes because there are no Model CN–235 airplanes with that serial number.

For Model CN–235–100 and –200 airplanes, the affected serial numbers are C–016 through C–073 inclusive. We have removed S/Ns C–001 through C–015 inclusive and C–074 for CN–235– 100 and –200 airplanes because there are no Model CN–235–100 and –200 with those serial numbers.

Conclusion

We reviewed the available 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 NPRM for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM.

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

Airbus Defense and Space S.A. has issued Airbus Military Alert Operators


## 34878 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations

Transmission AOT–CN235–76–0001, dated May 27, 2014. This service information describes repetitive replacements of each power lever and condition lever Teleflex cable having a certain part number with a new or serviceable part. This service information also provides a new life limit of 5,000 flight cycles. 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 3 airplanes of U.S. registry.

The rigging required by AD 2001–12– 18, and retained in this AD takes about 8 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the rigging that was required by AD 2001–12–18 is $680 per product.

The replacement required by AD 2001–12–18, and retained in this AD takes about 47 work-hours per product,at an average labor rate of $85 per workhour. Required parts cost about $1,444 per product. Based on these figures, the estimated cost of the replacement that was required by AD 2001–12–18 is $5,439 per product.

We also estimate that it would take about 47 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts would cost about $6,480 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $31,425, or $10,475 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: 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) 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001), and adding the following new AD:
2016–11–08 Airbus Defense and Space S.A. (formerly known as Construcciones Aeronauticas, S.A.): Amendment 39– 18535; Docket No. FAA–2015–8465; Directorate Identifier 2014–NM–239–AD.

(a) Effective Date

This AD is effective July 6, 2016.

(b) Affected ADs

This AD replaces AD 2001–12–18, Amendment 39–12274 (66 FR 33014, June 20, 2001) (‘‘AD 2001–12–18’’).
(c) Applicability

This AD applies to Airbus Defense and Space S.A. (formerly known as Construcciones Aeronauticas, S.A.) Model CN–235 airplanes, serial numbers C–001 through C–015 inclusive; and Model CN– 235–100 and –200 airplanes, serial numbers C–016 through C–073 inclusive; certificated in any category.
(d) Subject

Air Transport Association (ATA) of America Code 76, Engine Controls.

(e) Reason

This AD was prompted by reports of new occurrences of cable disruption on a certain part number; the disruption is caused by microcracks along the cable surface. We are issuing this AD to prevent fatigue of the engine control cables, leading to breakage of the cables, which could result in reduced controllability of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Retained Action for the Power Lever and Condition Lever Control Stops, With No Changes

This paragraph restates the requirements of paragraph (a) of AD 2001–12–18. Within 15 days after July 25, 2001 (the effective date of AD 2001–12–18): Rig the power lever and condition lever control stops, in accordance with CASA COM 235–140, Revision 01, dated March 21, 2000.
(h) New Requirement of This AD: Replacement

At the applicable compliance times specified in table 1 to paragraph (h) of this AD: Replace each power lever and condition lever Teleflex cable having part number (P/N) 72830–20 with a new or serviceable part, in accordance with Airbus Military Alert Operators Transmission AOT–CN235– 76–0001, dated May 27, 2014. Repeat the replacement thereafter at intervals not to exceed an accumulation of 5,000 total flight cycles on each Teleflex cable having P/N

72830–20.



### TABLE 

### 1 TO 

### P ARAGRAPH 

### (h) OF 

### T HIS 

### AD—R EPLACEMENT 

### C OMPLIANCE 

### T IME

Total flight cycles accumulated on the Teleflex cable having P/N 72830–20 (since first installation on an airplane) as of the effective date of this AD Compliance time

Fewer than 4,700 total flight cycles ......................................................... Before accumulating 5,000 total flight cycles. Equal to or more than 4,700 total flight cycles, but fewer than 6,000

total flight cycles. Within 300 flight cycles or 12 months after the effective date of this AD, whichever occurs first.


## 34879 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations

TABLE 

### 1 TO 

### P ARAGRAPH 

### (h) OF 

### T HIS 

### AD—R EPLACEMENT 

### C OMPLIANCE 

### T IME

### —Continued

Total flight cycles accumulated on the Teleflex cable having P/N 72830–20 (since first installation on an airplane) as of the effective date of this AD Compliance time

Equal to or more than 6,000 total flight cycles, but fewer than 7,000

total flight cycles. Within 200 flight cycles or 6 months after the effective date of this AD, whichever occurs first. Equal to or more than 7,000 total flight cycles ........................................ Within 100 flight cycles or 3 months after the effective date of this AD, whichever occurs first.

(i) Parts Installation Limitations

As of the effective date of this AD, no person may install, on any airplane, a Teleflex cable having P/N 72830–20, unless the cable has accumulated fewer than 5,000 total flight cycles since its first installation on an airplane.
(j) 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: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1112; 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 European Aviation Safety Agency (EASA); or EADS CASA’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(k) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0262, dated December 5, 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–2015–8465.
(l) 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 July 6, 2016.

(i) Airbus Military Alert Operators Transmission AOT–CN235–76–0001, dated May 27, 2014.

(ii) Reserved. (4) The following service information was approved for IBR on July 25, 2001 (66 FR 33014, June 20, 2001).

(i) CASA COM 235–140, Revision 01, dated March 21, 2000.

(ii) Reserved. (5) For service information identified in this AD, contact EADS–CASA, Military Transport Aircraft Division (MTAD), Integrated Customer Services (ICS), Technical Services, Avenida de Arago  ́ n 404, 28022 Madrid, Spain; telephone +34 91 585 55 84; fax +34 91 585 55 05; email MTA.TechnicalService@casa.eads.net;
Internet http://www.eads.net.

(6) 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.

(7) 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 May 20,

2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–12594 Filed 5–31–16; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 71**

**[Docket No. FAA–2016–0526; Airspace Docket No. 16–ASW–3]** 



### Amendment of Class E Airspace; Taos, **NM**

**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 Taos Regional Airport, Taos, NM. Decommissioning of non-directional radio beacon (NDB) and cancellation of the NDB approaches due to advances in Global Positioning System (GPS) capabilities have made this action necessary for the safety and management of Instrument Flight Rules (IFR) operations at Taos Regional Airport.

**DATES** 

### : Effective 0901 UTC, January 5, 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 7400.9 and publication of conforming amendments.

**ADDRESSES** 

### : 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 FAA Order 7400.9Z 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** 

### : 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.