Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) Helicopters, 11502-11504 [2017-02856]

Download as PDF 11502 Federal Register / Vol. 82, No. 36 / Friday, February 24, 2017 / Rules and Regulations 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] pmangrum on DSK3GDR082PROD with RULES RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 13 44 14:13 Feb 23, 2017 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). DATES: 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 https:// 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0674. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https:// 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. 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. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: U.S.C. 3506; 5 CFR 1320. VerDate Sep<11>2014 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. SUMMARY: Jkt 241001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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 E:\FR\FM\24FER1.SGM 24FER1 Federal Register / Vol. 82, No. 36 / Friday, February 24, 2017 / Rules and Regulations 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. pmangrum on DSK3GDR082PROD with RULES 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 VerDate Sep<11>2014 14:13 Feb 23, 2017 Jkt 241001 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. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 11503 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: ■ E:\FR\FM\24FER1.SGM 24FER1 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. pmangrum on DSK3GDR082PROD with RULES (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). VerDate Sep<11>2014 14:13 Feb 23, 2017 Jkt 241001 (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 9ASW-FTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under PO 00000 Frm 00004 Fmt 4700 Sfmt 9990 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 https://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 https:// 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: https:// 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 E:\FR\FM\24FER1.SGM 24FER1

Agencies

[Federal Register Volume 82, Number 36 (Friday, February 24, 2017)]
[Rules and Regulations]
[Pages 11502-11504]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-02856]


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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.

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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 https://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 https://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 https://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

[[Page 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 re-bonded 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 work-hour. 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

0
1. The authority citation for part 39 continues to read as follows:


[[Page 11504]]


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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  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-in-service (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 https://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 https://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: https://www.archives.gov/federal-register/cfr/ibr-locations.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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