40492 Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations 

(e) Reason 

This AD was prompted by the discovery of 

a number of incorrectly calibrated angle of 

attack (AOA) transducers installed in the 

stall protection system. We are issuing this 

AD to detect and replace incorrectly 

calibrated AOA transducers; incorrect 

calibration of the transducers could result in 

late activation of the stick pusher. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Replacement of AOA 

Transducers With No Changes 

This paragraph restates the requirements 

paragraph (g) of AD 2016–08–05, with no 

changes. Within 2,500 flight hours or 12 

months, whichever occurs first after May 18, 

2016 (the effective date of AD 2016–08–05), 

replace the AOA transducers identified in 

paragraph 1.A., ‘‘Effectivity,’’ of Bombardier 

Service Bulletin 670BA–27–069, dated March 

30, 2015, with correctly calibrated AOA 

transducers, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–069, dated March 

30, 2015. 

(h) Retained Parts Installation Prohibition, 

With a Change to the Affected Parts 

Language 

This paragraph restates the parts 

installation prohibition specified in 

paragraph (h) of AD 2016–08–05, with a 

change to the affected parts language. As of 

May 18, 2016 (the effective date of AD 2016– 

08–05), no person may install, on any 

airplane, an AOA transducer having a part 

number and serial number listed in 

paragraph 1.A., ‘‘Effectivity,’’ of Bombardier 

Service Bulletin 670BA–27–069, dated March 

30, 2015. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone: 516–228–7300; fax: 516–794– 

5531. 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, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

AD CF–2015–18, dated July 16, 2015, 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–2016–7265. 

(k) 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 May 18, 2016, (81 FR 

21709, April 13, 2016). 

(i) Bombardier Service Bulletin 670BA–27– 

069, dated March 30, 2015. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; Widebody Customer Response 

Center North America toll-free telephone: 1– 

866–538–1247 or direct-dial telephone: 1– 

514–855–2999; fax: 514–855–7401; email: 

ac.yul@aero.bombardier.com; Internet: 

http://www.bombardier.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/ibr-locations.html. 

Issued in Renton, Washington, on June 13, 

2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–14579 Filed 6–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0105; Directorate 

Identifier 2008–SW–58–AD; Amendment 39– 

18562; AD 2016–12–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2000–05– 

17 and AD 2001–04–12, which apply to 

Eurocopter France (now Airbus 

Helicopters) Model EC120B helicopters. 

AD 2000–05–17 and AD 2001–04–12 

required repetitive visual checks of the 

engine-to-main gearbox (MGB) coupling 

tube assembly (coupling tube) for a 

crack and replacing any cracked tube 

with an airworthy tube. This new AD 

requires removing certain engine mount 

parts from service, measuring the height 

of the engine mounting base for certain 

helicopters, replacing the engine mount 

if a certain height is exceeded, 

inspecting the flared coupling on certain 

helicopters for a crack, and replacing 

the coupling if it is cracked. Since we 

issued AD 2000–05–17 and AD 2001– 

04–12, there have been reports of 

additional cracks in coupling tubes. 

These actions are intended to prevent 

coupling tube failure, loss of engine 

drive, and a subsequent forced landing 

of the helicopter. 

DATES: This AD is effective July 27, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 27, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may view this referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0105. 


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Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov in Docket No. 

FAA–2014–0105; 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 Direction 

Generale de L’Aviation Civile (DGAC) 

AD, any incorporated-by-reference 

information, the economic evaluation, 

any comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document 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: 

James Blyn, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

james.blyn@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 29, 2015, we issued a notice 

of proposed rulemaking (NPRM) to 

amend 14 CFR part 39 to remove AD 

2000–05–17 (65 FR 13875, March 15, 

2000) and AD 2001–04–12 (66 FR 

13232, March 5, 2001) and add a new 

AD. AD 2000–05–17 applied to Model 

EC120B helicopters with engine 

coupling tube part number (P/N) 

C631A1002101 and required recurring 

inspections of each coupling tube for a 

crack and replacing any cracked 

coupling tube with a reinforced 

coupling tube P/N C631A1101101. AD 

2001–04–12 applied to Model EC120B 

helicopters with engine coupling tube 

P/N C631A1101101 and required 

repetitive visual checks of each 

coupling tube for a crack. AD 2000–05– 

17 and AD 2001–04–12 were prompted 

by reports of cracks on the reinforced 

coupling tube and were intended to 

prevent coupling tube failure, loss of 

engine drive, and a subsequent forced 

landing. 

The NPRM published in the Federal 

Register on June 16, 2015 (80 FR 34335). 

The NPRM was prompted by reports of 

additional cracks in coupling tubes. 

Eurocopter France (now Airbus 

Helicopters) determined that the 

washer-type engine mount may, in 

certain cases, induce excessive loading 

on the coupling tube, which results in 

binding that increases component wear 

of the inner diameter of the mounting 

base. Because of this, the DGAC, on 

behalf of the European Aviation Safety 

Agency (EASA), issued AD No. F–2003– 

325 R1, dated May 12, 2004, for Model 

EC120B helicopters with engine 

coupling tube, P/N C631A1101101, and 

with an engine mount containing 

certain parts listed in Eurocopter Alert 

Service Bulletin (ASB) No. 04A005, 

dated July 16, 2003. DGAC AD No. F– 

2003–325 R1 requires inspections for 

helicopters with an engine mount block 

modified in accordance with Eurocopter 

Service Bulletin (SB) No. 71–003, 

Revision 1, dated July 18, 2002; 

replacing any coupling tube that has a 

crack; and increasing the life limit of the 

coupling tube from 1,000 flight hours to 

20,000 flight hours. Also, DGAC AD No. 

F–2003–325 R1 requires, for helicopters 

with a new spring-loaded engine 

suspension modification in accordance 

with Eurocopter SB No. 71–005, 

Revision 0, dated May 14, 2004, 

increasing the life limit of the coupling 

tube to 20,000 flight hours and 

canceling the repetitive inspections of 

the coupling tube. 

The NPRM proposed to require, for 

helicopters with certain engine mounts, 

before further flight, removing from 

service certain engine mount parts and 

measuring the height of the engine 

mounting base. If the height is more 

than 10.5 millimeters, the NPRM 

proposed replacing the engine mount 

with an engine mount that does not 

have the affected parts. For certain other 

helicopters, the NPRM proposed to 

require within 25 hours time-in-serice 

(TIS) replacing the spring-type engine 

suspension system, dye-penetrant 

inspecting the flared coupling for a 

crack, and replacing any cracked flared 

coupling. The NPRM also proposed 

removing coupling tube P/N 

C631A1002101 from service and 

prohibiting installation of that coupling 

tube on any helicopter. 

Since the NPRM was issued, the FAA 

Southwest Regional Office has relocated 

and a group email address has been 

established for requesting an FAA 

alternative method of compliance for a 

helicopter of foreign design. We have 

revised the contact information 

throughout this final rule to reflect the 

new address and new email address. 

Comments 

After our NPRM (80 FR 34335, June 

16, 2015) was published, we received 

comments from one commenter. 

Request 

Airbus Helicopters disagrees with the 

proposed requirement to replace the 

spring-type engine suspension system in 

accordance with Eurocopter SB No. 71– 

005 for helicopters with an improved 

engine mount under Eurocopter SB No. 

71–003. Airbus Helicopters states there 

have been no coupling tube failures 

since incorporation of Eurocopter SB 

No. 71–003, and therefore the proposed 

requirement would not increase safety 

levels. 

We disagree. Installing the improved 

engine mount specified in Eurocopter 

SB No. 71–003 extends the compliance 

time for a recurring visual inspection of 

the coupling tube from 5 hours TIS to 

25 hours TIS. When issued, that 

recurring inspection was considered a 

short-term interim action until an 

effective modification or action was 

developed, approved, and available. 

Eurocopter SB No. 71–005 contained 

such an effective action to cancel that 

interim action and was developed and 

approved in May 2004. 

Airbus Helicopters requested that, if 

we mandate the proposed requirement 

to replace the spring-type engine 

suspension system in accordance with 

Eurocopter SB No. 71–005, we change 

the proposed compliance time from 25 

hours TIS to 18 months to allow for 

availability of parts. 

We disagree. Eurocopter SB No. 71– 

005 was approved May 13, 2004. The 

NPRM was published June 16, 2015. 

The substantial amount of time that has 

passed since the approval of the service 

information and publication of our 

NPRM provided operators with enough 

notice of our proposal to mandate that 

procedure such that availability of parts 

should not be an issue. 

FAA’s Determination 

This helicopter has been approved by 

the aviation authority of France and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, the DGAC on 

behalf of EASA, has kept the FAA 

informed of the situation described 

above. We are issuing this AD because 

we evaluated all information provided 

by the DGAC, reviewed the relevant 

information, considered the comments 

received, and determined the unsafe 

condition exists and is likely to exist or 

develop on other helicopters of this 

same type design and that air safety and 

the public interest require adopting the 

AD requirements as proposed. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter issued ASB No. 04A005, 

Revision 0, dated July 16, 2003, which 

prohibits, after June 30, 2004, operating 

an engine mount made up of the 

following parts: Support arm, P/N 

C714A1107201; swaged support arm, P/ 

N C714A1106201; left-hand support 

bracket, P/N C714A1101102; and rightVerDate Sep<11>2014 16:06 Jun 21, 2016 Jkt 238001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\22JNR1.SGM 22JNR1

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hand support bracket, P/N 

C714A1101103. ASB No. 04A005 also 

specifies measuring the height of the 

engine mounting base and, if the height 

is more than 10.5 millimeters, replacing 

the engine mount with an engine mount 

that does not have the specified P/N. 

ASB No. 04A005 does not apply to 

helicopters modified with an improved 

engine mount in accordance with SB 

No. 71–003. ASB No. 04A005 also does 

not apply to helicopters with a serial 

number 1170 or larger, as the specified 

engine mounts are not installed on those 

helicopters. 

Eurocopter also issued SB No. 71– 

005, Revision 0, dated May 14, 2004, 

which contains procedures to modify 

the spring-type engine suspension 

system and dye-penetrant inspect the 

flared coupling assembly. 

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. 

Other Related Service Information 

Eurocopter issued SB No. 71–003, 

Revision 1, dated July 18, 2002, which 

contains procedures to improve the 

engine mount. Eurocopter also issued 

ASB No. 05A003, Revision 2, dated July 

16, 2003, for helicopters that have not 

been modified with an improved engine 

mount in accordance with SB No. 71– 

003, which specifies inspecting the 

coupling tube for a crack every 5 hours 

and establishing a coupling tube life 

limit of 1,000 hours. For helicopters that 

have been modified with an improved 

engine mount, ASB No. 05A003 

specifies inspecting the coupling tube 

for a crack every 25 hours and 

increasing the coupling tube life limit to 

20,000 hours. ASB No. 05A003 was 

revised to Revision 3, dated May 11, 

2004, to specify an optional spring-type 

engine suspension modification and 

cancel the repetitive inspection for this 

modified configuration. 

Differences Between This AD and the 

DGAC AD 

This AD requires the installation of 

the spring-type engine suspension 

modification specified in Eurocopter SB 

No. 71–005 and does not require the 

repetitive inspection of the coupling 

tube and the engine mount base. This 

AD also does not require you to contact 

the manufacturer. 

Costs of Compliance 

We estimate that this AD will affect 

23 helicopters of the 115 helicopters of 

U.S. Registry. At an average labor rate of 

$85 per work-hour, we estimate that 

operators may incur the following costs 

in order to comply with this AD. 

Installing new mounting arms and 

brackets requires about 12 work-hours 

and required parts cost $9,194, for a 

total cost per helicopter of $10,214 and 

$234,922 for the U.S. fleet. Installing the 

mounting spring kit requires about 14 

work-hours and required parts cost 

$14,621, for a total cost per helicopter 

of $15,811 and $363,653 for the U.S. 

fleet. Dye-penetrant inspecting the 

coupling tube requires about 1 workhour for a cost per helicopter of $85 and 

$1,955 for the U.S. fleet. 

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 have 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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that a regulatory, 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2000–05–17, Amendment 39– 

11627 (65 FR 13875, March 15, 2000); 

and AD 2001–04–12, Amendment 39– 

12131 (66 FR 13232, March 5, 2001); 

and 

■ b. Adding the following new AD: 

2016–12–13 Airbus Helicopters (Previously 

Eurocopter France): Amendment 39– 

18562; Docket No. FAA–2014–0105; 

Directorate Identifier 2008–SW–58–AD. 

(a) Applicability 

This AD applies to Model EC120B 

helicopters with an engine-to-main gearbox 

coupling tube assembly (coupling tube), part 

number (P/N) C631A1101101 or P/N 

C631A1002101, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a coupling tube. This condition 

could result in coupling tube failure, loss of 

engine drive, and a subsequent forced 

landing of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2000–05–17, 

Amendment 39–11627 (65 FR 13875, March 

15, 2000) and AD 2001–04–12, Amendment 

39–12131 (66 FR 13232, March 5, 2001). 

(d) Effective Date 

This AD becomes effective July 27, 2016. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) For helicopters with a serial number up 

to and including 1169, not modified with an 

improvement of the engine mount in 

accordance with Eurocopter Service Bulletin 

(SB) No. 71–003, Revision 1, dated July 18, 

2002 (SB 71–003), or not modified by 

installing a spring-type engine suspension 

system in accordance with Eurocopter SB No. 

71–005, Revision 0, dated May 14, 2004 (SB 

71–005), before further flight: 


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Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations 40495 

(i) Remove from service the following 

engine mount parts: 

(A) Support arm, P/N C714A1107201; 

(B) Swaged support arm, P/N 

C714A1106201; 

(C) Left-hand support bracket, P/N 

C714A1101102; and 

(D) Right-hand support bracket, P/N 

C714A1101103. 

(ii) Measure the height of the engine 

mounting base as depicted in Figure 1 of 

Eurocopter Alert SB No. 04A005, Revision 0, 

dated July 16, 2003. If the height is more than 

10.5 millimeters, replace the engine mount 

with an engine mount that does not have the 

parts identified in paragraph (f)(1)(i) of this 

AD. 

(2) For helicopters with a serial number 

1170 and larger or helicopters modified with 

an improvement of the engine mount in 

accordance with SB 71–003: 

(i) Within 25 hours TIS, replace the springtype engine suspension system and perform 

a dye-penetrant inspection of the flared 

coupling for a crack by following the 

Accomplishment Instructions, paragraphs 

2.B.2.a through 2.B.2.c of SB 71–005. 

(ii) If there is a crack in the flared coupling, 

before further flight, replace the coupling 

with an airworthy coupling. 

(3) For helicopters with coupling tube, P/ 

N C631A1002101, installed, before further 

flight, remove coupling tube, P/N 

C631A1002101, from service. Do not install 

coupling tube, P/N C631A1002101, on any 

helicopter. 

(g) Special Flight Permits 

Special flight permits may be issued 

provided there are no cracks in the coupling 

tube attachment fitting. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: James Blyn, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 9- 

ASW-FTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

(1) Eurocopter Alert Service Bulletin (ASB) 

No. 05A003, Revision 2, dated July 16, 2003; 

Eurocopter ASB No. 05A003, Revision 3, 

dated May 11, 2004; and Eurocopter Service 

Bulletin No. 71–003, Revision 1, dated July 

18, 2002; which are not incorporated by 

reference, contain additional information 

about the subject of this final rule. For 

Eurocopter service information identified in 

this final rule, contact Airbus Helicopters, 

2701 N. Forum Drive, Grand Prairie, TX 

75052; telephone (972) 641–0000 or (800) 

232–0323; fax (972) 641–3775; or at http:// 

www.airbushelicopters.com/techpub. You 

may review a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 

(2) The subject of this AD is addressed in 

Direction Generale de L’Aviation Civile 

(DGAC) AD No. F–2003–325 R1, Revision 1, 

dated May 12, 2004. You may view the 

DGAC AD on the Internet at http:// 

www.regulations.gov in Docket No. FAA– 

2014–0105. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6310, Engine/Transmission Coupling— 

Coupling Tube, Engine Mount, and Engine 

Mount Base. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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. 

(i) Eurocopter Alert Service Bulletin No. 

04A005, Revision 0, dated July 16, 2003. 

(ii) Eurocopter Service Bulletin No. 71– 

005, Revision 0, dated May 14, 2004. 

(3) For Eurocopter service information 

identified in this final rule, contact Airbus 

Helicopters, 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641–0000 

or (800) 232–0323; fax (972) 641–3775; or at 

http://www.airbushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) 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 Fort Worth, Texas, on June 9, 

2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–14467 Filed 6–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 31084; Amdt. No. 527] 

IFR Altitudes; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts 

miscellaneous amendments to the 

required IFR (instrument flight rules) 

altitudes and changeover points for 

certain Federal airways, jet routes, or 

direct routes for which a minimum or 

maximum en route authorized IFR 

altitude is prescribed. This regulatory 

action is needed because of changes 

occurring in the National Airspace 

System. These changes are designed to 

provide for the safe and efficient use of 

the navigable airspace under instrument 

conditions in the affected areas. 

DATES: Effective 0901 UTC, July 21, 

2016. 

FOR FURTHER INFORMATION CONTACT: 

Richard A. Dunham, Flight Procedure 

Standards Branch (AMCAFS–420), 

Flight Technologies and Programs 

Division, Flight Standards Service, 

Federal Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd., Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082 Oklahoma City, OK 73125) 

telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This 

amendment to part 95 of the Federal 

Aviation Regulations (14 CFR part 95) 

amends, suspends, or revokes IFR 

altitudes governing the operation of all 

aircraft in flight over a specified route 

or any portion of that route, as well as 

the changeover points (COPs) for 

Federal airways, jet routes, or direct 

routes as prescribed in part 95. 

The Rule 

The specified IFR altitudes, when 

used in conjunction with the prescribed 

changeover points for those routes, 

ensure navigation aid coverage that is 

adequate for safe flight operations and 

free of frequency interference. The 

reasons and circumstances that create 

the need for this amendment involve 

matters of flight safety and operational 

efficiency in the National Airspace 

System, are related to published 

aeronautical charts that are essential to 

the user, and provide for the safe and 

efficient use of the navigable airspace. 

In addition, those various reasons or 

circumstances require making this 

amendment effective before the next 

scheduled charting and publication date 

of the flight information to assure its 

timely availability to the user. The 

effective date of this amendment reflects 

those considerations. In view of the 

close and immediate relationship 

between these regulatory changes and 

safety in air commerce, I find that notice 

and public procedure before adopting 

this amendment are impracticable and 

contrary to the public interest and that 

good cause exists for making the 


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