11502 Federal Register / Vol. 82, No. 36 / Friday, February 24, 2017 / Rules and Regulations 

13 44 U.S.C. 3506; 5 CFR 1320. 

the Board has determined that it is 

unnecessary to publish a general notice 

of proposed rulemaking for this final 

rule. Accordingly, the RFA’s 

requirements relating to an initial and 

final regulatory flexibility analysis do 

not apply. 

Paperwork Reduction Act 

In accordance with the Paperwork 

Reduction Act of 1995,13 the Board has 

reviewed this final rule. No collections 

of information pursuant to the 

Paperwork Reduction Act are contained 

in the final rule. 

List of Subjects in 12 CFR Part 209 

Banks and banking, Federal Reserve 

System, Reporting and recordkeeping 

requirements, Securities. 

Authority and Issuance 

For the reasons set forth in the 

preamble, the Board amends Regulation 

I, 12 CFR part 209, as follows: 

PART 209—ISSUE AND 

CANCELLATION OF FEDERAL 

RESERVE BANK CAPITAL STOCK 

(REGULATION I) 

■ 1. The authority citation for part 209 

continues to read as follows: 

Authority: 12 U.S.C. 12 U.S.C. 222, 248, 

282, 286–288, 289, 321, 323, 327–328, and 

466. 

■ 2. In part 209, remove all references to 

‘‘$10,000,000,000’’ and add in their 

place ‘‘$10,122,000,000’’, wherever they 

appear. 

By order of the Board of Governors of the 

Federal Reserve System, February 17, 2017. 

Robert deV. Frierson, 

Secretary of the Board. 

[FR Doc. 2017–03568 Filed 2–23–17; 8:45 am] 

BILLING CODE 6210–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0674; Directorate 

Identifier 2014–SW–019–AD; Amendment 

39–18792; AD 2017–03–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2014–05– 

06 for Eurocopter Deutschland GmbH 

(ECD) (now Airbus Helicopters 

Deutschland GmbH) Model EC135 and 

MBB–BK 117 C–2 helicopters to correct 

an error in the compliance time. AD 

2014–05–06 required inspecting the 

flight-control bearings and installing 

bushings and washers. This AD requires 

the same actions. These actions are 

intended to prevent an unsafe condition 

on these products. 

DATES: This AD is effective March 31, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 14, 2014 (79 FR 13196, 

March 10, 2014). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 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 the 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–2015– 

0674. 

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– 

0674; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy, Fort Worth, TX 76177; telephone 

(817) 222–5110; email matthew.fuller@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2014–05–06, 

Amendment 39–17779 (79 FR 13196, 

March 10, 2014) and add a new AD. AD 

2014–05–06 required inspecting the 

flight control bearings repetitively, 

replacing any loose bearing with an 

airworthy flight control bearing, and 

installing bushings and washers. The 

NPRM published in the Federal 

Register on March 30, 2015 (80 FR 

16603). The NPRM proposed to retain 

all of the required actions and correct an 

error in the compliance time. AD 2014– 

05–06 should have required installing 

the bushings and washers on Model 

EC135 helicopters within the next 100 

hours time-in-service or at the next 

annual inspection, whichever occurs 

first. However, we omitted the word 

‘‘first’’ from that sentence, which 

changes the meaning of the required 

compliance time. 

AD 2014–05–06 was prompted by the 

discovery of loose flight control bearings 

because of incorrect installation. This 

condition could result in the affected 

control lever shifting, contacting the 

helicopter structure. The actions in AD 

2014–05–06 were intended to prevent 

this unsafe condition, which could 

reduce control of the helicopter. 

Also since we issued AD 2014–05–06, 

ECD changed its name to Airbus 

Helicopters Deutschland GmbH (Airbus 

Helicopters). This AD reflects that 

change and updates the contact 

information to obtain service 

documentation. 

Comments 

After our NPRM (80 FR 16603, March 

30, 2015) was published, we received 

comments from one commenter. 

Request 

Airbus Helicopters first requested 

revising the compliance times for the 

repetitive inspections to match that in 

its current service information. For the 

Model EC135 P1, P2, P2+, T1, T2, and 

T2+ helicopters, Airbus Helicopters 

requested increasing the 800 hour 

interval to 1000 hours with an 

additional 10% margin. For MBB–BK 

117 C–2 helicopters, Airbus Helicopters 

requested increasing the 600 hour 

interval to 800 hours with an additional 

10% margin. 

We disagree. Airbus Helicopters did 

not provide any technical justification 

to support this request. The final rule 

has not been changed as a result of this 

comment. 

Airbus Helicopters also requested that 

if any bearing is loose, we require 


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Federal Register / Vol. 82, No. 36 / Friday, February 24, 2017 / Rules and Regulations 11503 

replacing the lever or rebonding the 

affected bearing in accordance with its 

maintenance instructions. 

We agree with the comment but 

disagree that a change to the AD is 

necessary. If there is a loose bearing, the 

AD requires replacing it with an 

airworthy part. If a bearing can be rebonded in a manner acceptable to the 

FAA, then it would be an airworthy 

part. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA, 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 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed with the changes described 

previously. These changes are 

consistent with the intent of the 

proposals in the NPRM (80 FR 16603, 

March 30, 2015), and will not increase 

the economic burden on any operator 

nor increase the scope of this AD. 

Differences Between This AD and the 

EASA AD 

Differences between this AD and the 

EASA AD are: 

• The EASA AD is applicable to the 

EC 635 helicopter, whereas this AD is 

not because the EC 635 helicopter is not 

type certificated in the U.S. 

• The EASA AD requires an initial 

inspection within 50 flight hours or one 

month, whichever occurs first after May 

31, 2008, and a modification within the 

next 12 months. This AD requires the 

modification within 100 hours TIS or at 

the next annual inspection, whichever 

occurs first, and no inspection until 

after the modification has been 

accomplished. 

• The EASA AD specifies repetitive 

inspection intervals not to exceed 800 

hours TIS or 12 months, plus a 10% 

percent margin, whichever occurs first, 

for Model EC135 helicopters and 600 

hours TIS or 12 months, plus a 10% 

percent margin, whichever occurs first, 

for the Model MBB–BK 117 C–2 

helicopters. This AD requires repetitive 

inspection intervals not to exceed 800 

hours TIS or 36 months, whichever 

occurs first, for Model EC135 

helicopters and 600 hours TIS or 24 

months, whichever occurs first, for 

Model MBB–BK 117 C–2 helicopters. 

• The EASA AD applies to all Model 

EC135 and Model MBB–BK 117 C–2 

helicopters, while this AD applies to 

certain serial-numbered Model EC135 

and Model MBB–BK 117 C–2 

helicopters, as recommended by the 

appropriate ECD ASB. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter (now Airbus Helicopters) 

has issued Alert Service Bulletin (ASB) 

MBB BK117 C–2–67A–010, Revision 3, 

dated February 8, 2010 for Model MBB– 

BK 117 C–2 helicopters, and ASB 

EC135–67A–019, Revision 3, dated 

December 16, 2009 for Model EC135 

helicopters. These ASBs specify: 

• Within the next 50 flight hours 

(FHs), inspecting the affected bearings 

and, if necessary, rebonding any 

affected bearings or replacing the lever 

assembly. 

• Within 12 months, retrofitting 

bushings and washers on the levers to 

prevent movement of the bearings. 

• After the retrofit, repeating the 

inspection every 800 FHs or 36 months 

for the Model EC135 helicopters, 

whichever comes first, and 600 FHs or 

24 months, whichever comes first, for 

the Model MBB–BK 117 C–2 

helicopters. 

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 175 

Model EC135 and 112 Model MBB–BK 

117 C–2 helicopters of U.S. Registry and 

that labor costs average $85 per workhour. Based on these estimates, we 

expect the following costs: 

• For EC135 helicopters, it takes 

about 32 work-hours to perform the 

modification. Parts cost about $312. The 

total cost for the modification is about 

$3,032 per helicopter and $530,600 for 

the U.S. operator fleet. The repetitive 

inspections require 6.5 work-hours for a 

cost of about $553 per helicopter and 

about $96,775 for the fleet per 

inspection cycle. 

• For MBB–BK 117 C–2 helicopters, it 

takes about 32 work-hours to perform 

the modification. Parts cost about $396. 

The total cost for the modification is 

$3,116 per helicopter and $348,992 for 

the U.S. operator fleet. The cost for the 

repetitive inspections thereafter is about 

$85 per helicopter and $9,520 for the 

fleet per inspection cycle. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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 it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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: 


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11504 Federal Register / Vol. 82, No. 36 / Friday, February 24, 2017 / Rules and Regulations 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2014–05–06, Amendment 39–17779 (79 

FR 13196, March 10, 2014), and adding 

the following new AD: 

2017–03–01 Airbus Helicopters 

Deutschland GmbH (Previously 

Eurocopter Deutschland GmbH): 

Amendment 39–18792; Docket No. 

FAA–2015–0674; Directorate Identifier 

2014–SW–019–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: 

(1) Model EC135 P1, P2, P2+, T1, T2, and 

T2+ helicopters, serial number (S/N) 0005 

through 00829, with a tail rotor control lever, 

part number (P/N) L672M2802205 or 

L672M1012212; cyclic control lever, P/N 

L671M1005250; collective control lever 

assembly, P/N L671M2020108; or collective 

control plate, P/N L671M5040207; installed; 

and 

(2) Model MBB–BK 117 C–2 helicopters, 

S/N 9004 through 9310, with a tail rotor 

control lever assembly, P/N B672M1007101 

or B672M1807101; tail rotor control lever, P/ 

N B672M1002202 or L672M2802205; or 

lateral control lever assembly, P/N 

B670M1008101, installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

incorrectly installed flight control bearings. 

This condition could cause the affected 

control lever to shift and contact the 

helicopter structure, resulting in reduced 

control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2014–05–06, 

Amendment 39–17779 (79 FR 13196, March 

10, 2014). 

(d) Effective Date 

This AD becomes effective March 31, 2017. 

(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 Model EC135 P1, P2, P2+, T1, T2, 

and T2+ helicopters: 

(i) Within the next 100 hours time-inservice (TIS) or at the next annual inspection, 

whichever occurs first, modify the left-hand 

(LH) and right-hand (RH) guidance units and 

the cyclic shaft by installing bushings and 

washers to prevent shifting of the bearings in 

the axial direction as follows: 

(A) Remove and disassemble the LH 

guidance unit and install a bushing, P/N 

L672M1012260, between the bearing block 

and the lever of the LH guidance unit as 

depicted in Detail A of Figure 5 of Eurocopter 

Alert Service Bulletin EC135–67A–019, 

Revision 3, dated December 16, 2009 (EC135 

ASB). 

(B) For helicopters without a yaw brake, 

remove and disassemble the RH guidance 

unit and install a bushing, P/N 

L672M1012260, between the bearing block 

and the lever as depicted in Detail B of 

Figure 5 of EC135 ASB. 

(C) Remove and disassemble the cyclic 

shaft and install a washer, P/N 

L671M1005260, between the bearing block 

and the lever as depicted in Detail C of 

Figure 6 of EC135 ASB. 

(D) Remove the collective control rod from 

the bellcrank and install a washer, P/N 

L221M1042208, on each side of the collective 

control rod and bellcrank as depicted in 

Detail D of Figure 6 of EC135 ASB. 

(E) At intervals not to exceed 800 hours 

TIS or 36 months, whichever occurs first, 

inspect the bearings in the LH guidance unit, 

RH guidance unit, cyclic control, upper 

guidance unit, and linear voltage differential 

transducer plate for play. If any bearing is 

loose, replace the affected bearing with an 

airworthy bearing. 

(2) For Model MBB–BK 117 C–2 

helicopters: 

(i) Within the next 100 hours TIS or at the 

next annual inspection, whichever occurs 

first, modify the LH and RH guidance units 

and the lateral control lever by installing 

bushings and washers to prevent shifting of 

the bearings in the axial direction as follows: 

(A) Remove and disassemble the RH 

guidance unit and install a bushing, P/N 

L672M1012260, between the lever and the 

bracket as depicted in Detail B of Figure 4 of 

Eurocopter Alert Service Bulletin MBB 

BK117 C–2–67A–010, Revision 3, dated 

February 8, 2010 (BK117 ASB). Remove and 

disassemble the LH guidance unit and install 

a bushing, P/N L672M1012260, between the 

lever and the bracket as depicted in Detail C 

of Figure 4 of BK117 ASB. 

(B) Remove the lateral control lever and 

install new bushings in accordance with the 

Accomplishment Instructions, paragraphs 

3.C(9)(a) through 3.C(9)(g), of BK 117 ASB. 

(C) Identify the modified lever assembly by 

writing ‘‘MBB BK117 C–2–67A–010’’ on the 

lever with permanent marking pen and 

protect with a single layer of lacquer (CM 

421or equivalent). 

(D) Apply corrosion preventive paste (CM 

518 or equivalent) on the shank of the screws 

and install airworthy parts as depicted in 

Figure 5 of BK117 ASB. 

(E) At intervals not to exceed 600 hours 

TIS or 24 months, whichever occurs first, 

inspect the bearings in the RH guidance unit, 

LH guidance unit, and lateral control 

guidance unit for play. If any bearing is loose, 

replace the affected bearing with an 

airworthy bearing. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management 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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0058, dated March 30, 2010. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2015–0674. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710, Main Rotor Control. 

(j) 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 the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(3) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information listed in 

this paragraph on April 14, 2014 (79 FR 

13196, March 10, 2014). 

(i) Eurocopter Alert Service Bulletin 

EC135–67A–019, Revision 3, dated December 

16, 2009. 

(ii) Eurocopter Alert Service Bulletin MBB 

BK117 C–2–67A–010, Revision 3, dated 

February 8, 2010. 

(4) For service information identified in 

this final rule, contact Airbus Helicopters, 

Inc., 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. 

(5) 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. 

(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 Fort Worth, Texas, on January 25, 

2017. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2017–02856 Filed 2–23–17; 8:45 am] 

BILLING CODE 4910–13–P 


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