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– 


sradovich on DSK3TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34877 

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 


sradovich on DSK3TPTVN1PROD with RULES
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 PARAGRAPH (h) OF THIS AD—REPLACEMENT COMPLIANCE TIME

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. 


sradovich on DSK3TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34879 

TABLE 1 TO PARAGRAPH (h) OF THIS AD—REPLACEMENT COMPLIANCE TIME—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. 


sradovich on DSK3TPTVN1PROD with RULES