82 FR 11502 - Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 36 (February 24, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 36 (February 24, 2017)
| Page Range | 11502-11504 | |
| FR Document | 2017-02856 |
[Federal Register Volume 82, Number 36 (Friday, February 24, 2017)] [Rules and Regulations] [Pages 11502-11504] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-02856] ======================================================================= ----------------------------------------------------------------------- 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 [email protected]. 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 [email protected]. (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/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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the Board has determined that it is SUMMARY: We are superseding Discussion
unnecessary to publish a general notice airworthiness directive (AD) 2014–05– We issued a notice of proposed
of proposed rulemaking for this final 06 for Eurocopter Deutschland GmbH rulemaking (NPRM) to amend 14 CFR
rule. Accordingly, the RFA’s (ECD) (now Airbus Helicopters part 39 to remove AD 2014–05–06,
requirements relating to an initial and Deutschland GmbH) Model EC135 and Amendment 39–17779 (79 FR 13196,
final regulatory flexibility analysis do MBB–BK 117 C–2 helicopters to correct March 10, 2014) and add a new AD. AD
not apply. an error in the compliance time. AD 2014–05–06 required inspecting the
2014–05–06 required inspecting the flight control bearings repetitively,
Paperwork Reduction Act
flight-control bearings and installing replacing any loose bearing with an
In accordance with the Paperwork bushings and washers. This AD requires
Reduction Act of 1995,13 the Board has airworthy flight control bearing, and
the same actions. These actions are installing bushings and washers. The
reviewed this final rule. No collections intended to prevent an unsafe condition
of information pursuant to the NPRM published in the Federal
on these products. Register on March 30, 2015 (80 FR
Paperwork Reduction Act are contained
in the final rule. DATES: This AD is effective March 31, 16603). The NPRM proposed to retain
2017. all of the required actions and correct an
List of Subjects in 12 CFR Part 209 The Director of the Federal Register error in the compliance time. AD 2014–
Banks and banking, Federal Reserve approved the incorporation by reference 05–06 should have required installing
System, Reporting and recordkeeping of certain publications listed in this AD the bushings and washers on Model
requirements, Securities. as of April 14, 2014 (79 FR 13196, EC135 helicopters within the next 100
March 10, 2014). hours time-in-service or at the next
Authority and Issuance annual inspection, whichever occurs
For the reasons set forth in the ADDRESSES: For service information first. However, we omitted the word
preamble, the Board amends Regulation identified in this final rule, contact ‘‘first’’ from that sentence, which
I, 12 CFR part 209, as follows: Airbus Helicopters, Inc., 2701 N. Forum changes the meaning of the required
Drive, Grand Prairie, TX 75052; compliance time.
PART 209—ISSUE AND telephone (972) 641–0000 or (800) 232– AD 2014–05–06 was prompted by the
CANCELLATION OF FEDERAL 0323; fax (972) 641–3775; or at http:// discovery of loose flight control bearings
RESERVE BANK CAPITAL STOCK www.airbushelicopters.com/techpub. because of incorrect installation. This
(REGULATION I) You may review the referenced service condition could result in the affected
information at the FAA, Office of the control lever shifting, contacting the
■ 1. The authority citation for part 209 Regional Counsel, Southwest Region, helicopter structure. The actions in AD
continues to read as follows: 10101 Hillwood Pkwy, Room 6N–321, 2014–05–06 were intended to prevent
Authority: 12 U.S.C. 12 U.S.C. 222, 248, Fort Worth, TX 76177. It is also this unsafe condition, which could
282, 286–288, 289, 321, 323, 327–328, and available on the Internet at http:// reduce control of the helicopter.
466. www.regulations.gov by searching for Also since we issued AD 2014–05–06,
■ 2. In part 209, remove all references to and locating Docket No. FAA–2015– ECD changed its name to Airbus
‘‘$10,000,000,000’’ and add in their 0674. Helicopters Deutschland GmbH (Airbus
place ‘‘$10,122,000,000’’, wherever they Examining the AD Docket Helicopters). This AD reflects that
appear. change and updates the contact
By order of the Board of Governors of the You may examine the AD docket on information to obtain service
Federal Reserve System, February 17, 2017. the Internet at http:// documentation.
Robert deV. Frierson, www.regulations.gov by searching for
and locating Docket No. FAA–2015– Comments
Secretary of the Board.
0674; or in person at the Docket After our NPRM (80 FR 16603, March
[FR Doc. 2017–03568 Filed 2–23–17; 8:45 am]
Operations Office between 9 a.m. and 5 30, 2015) was published, we received
BILLING CODE 6210–01–P
p.m., Monday through Friday, except comments from one commenter.
Federal holidays. The AD docket
contains this AD, the European Aviation Request
DEPARTMENT OF TRANSPORTATION Safety Agency (EASA) AD, any Airbus Helicopters first requested
incorporated-by-reference service revising the compliance times for the
Federal Aviation Administration
information, the economic evaluation, repetitive inspections to match that in
any comments received, and other its current service information. For the
14 CFR Part 39
information. The street address for the Model EC135 P1, P2, P2+, T1, T2, and
[Docket No. FAA–2015–0674; Directorate Docket Operations Office (phone: 800– T2+ helicopters, Airbus Helicopters
Identifier 2014–SW–019–AD; Amendment 647–5527) is U.S. Department of requested increasing the 800 hour
39–18792; AD 2017–03–01] Transportation, Docket Operations interval to 1000 hours with an
RIN 2120–AA64 Office, M–30, West Building Ground additional 10% margin. For MBB–BK
Floor, Room W12–140, 1200 New Jersey 117 C–2 helicopters, Airbus Helicopters
Airworthiness Directives; Airbus Avenue SE., Washington, DC 20590. requested increasing the 600 hour
Helicopters Deutschland GmbH interval to 800 hours with an additional
FOR FURTHER INFORMATION CONTACT: Matt
(Previously Eurocopter Deutschland 10% margin.
Fuller, Senior Aviation Safety Engineer,
pmangrum on DSK3GDR082PROD with RULES
GmbH) Helicopters We disagree. Airbus Helicopters did
Safety Management Group, Rotorcraft
AGENCY: Federal Aviation Directorate, FAA, 10101 Hillwood not provide any technical justification
Administration (FAA), DOT. Pkwy, Fort Worth, TX 76177; telephone to support this request. The final rule
(817) 222–5110; email matthew.fuller@ has not been changed as a result of this
ACTION: Final rule.
faa.gov. comment.
Airbus Helicopters also requested that
13 44 U.S.C. 3506; 5 CFR 1320. SUPPLEMENTARY INFORMATION: if any bearing is loose, we require
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Authority: 49 U.S.C. 106(g), 40113, 44701. (B) For helicopters without a yaw brake, 14 CFR part 91, subpart K, we suggest that
remove and disassemble the RH guidance you notify your principal inspector, or
§ 39.13 [Amended] unit and install a bushing, P/N lacking a principal inspector, the manager of
L672M1012260, between the bearing block the local flight standards district office or
■ 2. The FAA amends § 39.13 by and the lever as depicted in Detail B of
removing Airworthiness Directive (AD) certificate holding district office, before
Figure 5 of EC135 ASB.
2014–05–06, Amendment 39–17779 (79 operating any aircraft complying with this
(C) Remove and disassemble the cyclic
FR 13196, March 10, 2014), and adding shaft and install a washer, P/N AD through an AMOC.
the following new AD: L671M1005260, between the bearing block (h) Additional Information
and the lever as depicted in Detail C of
2017–03–01 Airbus Helicopters Figure 6 of EC135 ASB. The subject of this AD is addressed in
Deutschland GmbH (Previously (D) Remove the collective control rod from European Aviation Safety Agency (EASA) AD
Eurocopter Deutschland GmbH): the bellcrank and install a washer, P/N No. 2010–0058, dated March 30, 2010. You
Amendment 39–18792; Docket No. L221M1042208, on each side of the collective may view the EASA AD on the Internet at
FAA–2015–0674; Directorate Identifier control rod and bellcrank as depicted in http://www.regulations.gov in Docket No.
2014–SW–019–AD. Detail D of Figure 6 of EC135 ASB. FAA–2015–0674.
(a) Applicability (E) At intervals not to exceed 800 hours
TIS or 36 months, whichever occurs first, (i) Subject
This AD applies to the following
inspect the bearings in the LH guidance unit, Joint Aircraft Service Component (JASC)
helicopters, certificated in any category:
RH guidance unit, cyclic control, upper Code: 6710, Main Rotor Control.
(1) Model EC135 P1, P2, P2+, T1, T2, and
guidance unit, and linear voltage differential
T2+ helicopters, serial number (S/N) 0005
transducer plate for play. If any bearing is (j) Material Incorporated by Reference
through 00829, with a tail rotor control lever,
loose, replace the affected bearing with an (1) The Director of the Federal Register
part number (P/N) L672M2802205 or
airworthy bearing.
L672M1012212; cyclic control lever, P/N approved the incorporation by reference of
(2) For Model MBB–BK 117 C–2
L671M1005250; collective control lever the service information listed in this
helicopters:
assembly, P/N L671M2020108; or collective paragraph under 5 U.S.C. 552(a) and 1 CFR
(i) Within the next 100 hours TIS or at the
control plate, P/N L671M5040207; installed; part 51.
next annual inspection, whichever occurs
and (2) You must use the following service
first, modify the LH and RH guidance units
(2) Model MBB–BK 117 C–2 helicopters,
and the lateral control lever by installing information to do the actions required by this
S/N 9004 through 9310, with a tail rotor
bushings and washers to prevent shifting of AD, unless the AD specifies otherwise.
control lever assembly, P/N B672M1007101
the bearings in the axial direction as follows: (3) The Director of the Federal Register
or B672M1807101; tail rotor control lever, P/
(A) Remove and disassemble the RH previously approved the incorporation by
N B672M1002202 or L672M2802205; or
guidance unit and install a bushing, P/N reference of the service information listed in
lateral control lever assembly, P/N
L672M1012260, between the lever and the this paragraph on April 14, 2014 (79 FR
B670M1008101, installed.
bracket as depicted in Detail B of Figure 4 of
13196, March 10, 2014).
(b) Unsafe Condition Eurocopter Alert Service Bulletin MBB
(i) Eurocopter Alert Service Bulletin
This AD defines the unsafe condition as BK117 C–2–67A–010, Revision 3, dated
February 8, 2010 (BK117 ASB). Remove and EC135–67A–019, Revision 3, dated December
incorrectly installed flight control bearings. 16, 2009.
This condition could cause the affected disassemble the LH guidance unit and install
a bushing, P/N L672M1012260, between the (ii) Eurocopter Alert Service Bulletin MBB
control lever to shift and contact the
lever and the bracket as depicted in Detail C BK117 C–2–67A–010, Revision 3, dated
helicopter structure, resulting in reduced
control of the helicopter. of Figure 4 of BK117 ASB. February 8, 2010.
(B) Remove the lateral control lever and (4) For service information identified in
(c) Affected ADs install new bushings in accordance with the this final rule, contact Airbus Helicopters,
This AD supersedes AD 2014–05–06, Accomplishment Instructions, paragraphs Inc., 2701 N. Forum Drive, Grand Prairie, TX
Amendment 39–17779 (79 FR 13196, March 3.C(9)(a) through 3.C(9)(g), of BK 117 ASB. 75052; telephone (972) 641–0000 or (800)
10, 2014). (C) Identify the modified lever assembly by 232–0323; fax (972) 641–3775; or at http://
writing ‘‘MBB BK117 C–2–67A–010’’ on the
(d) Effective Date www.airbushelicopters.com/techpub.
lever with permanent marking pen and
protect with a single layer of lacquer (CM (5) You may view this service information
This AD becomes effective March 31, 2017.
421or equivalent). at FAA, Office of the Regional Counsel,
(e) Compliance (D) Apply corrosion preventive paste (CM Southwest Region, 10101 Hillwood Pkwy,
You are responsible for performing each 518 or equivalent) on the shank of the screws Room 6N–321, Fort Worth, TX 76177. For
action required by this AD within the and install airworthy parts as depicted in information on the availability of this
specified compliance time unless it has Figure 5 of BK117 ASB. material at the FAA, call (817) 222–5110.
already been accomplished prior to that time. (E) At intervals not to exceed 600 hours (6) You may view this service information
TIS or 24 months, whichever occurs first, that is incorporated by reference at the
(f) Required Actions inspect the bearings in the RH guidance unit, National Archives and Records
(1) For Model EC135 P1, P2, P2+, T1, T2, LH guidance unit, and lateral control Administration (NARA). For information on
and T2+ helicopters: guidance unit for play. If any bearing is loose,
(i) Within the next 100 hours time-in- the availability of this material at NARA, call
replace the affected bearing with an
service (TIS) or at the next annual inspection, airworthy bearing. (202) 741–6030, or go to: http://
whichever occurs first, modify the left-hand www.archives.gov/federal-register/cfr/ibr-
(LH) and right-hand (RH) guidance units and (g) Alternative Methods of Compliance locations.html.
the cyclic shaft by installing bushings and (AMOCs)
Issued in Fort Worth, Texas, on January 25,
washers to prevent shifting of the bearings in (1) The Manager, Safety Management
2017.
the axial direction as follows: Group, FAA, may approve AMOCs for this
pmangrum on DSK3GDR082PROD with RULES
(A) Remove and disassemble the LH AD. Send your proposal to: Matt Fuller, Lance T. Gant,
guidance unit and install a bushing, P/N Senior Aviation Safety Engineer, Safety Manager, Rotorcraft Directorate, Aircraft
L672M1012260, between the bearing block Management Group, Rotorcraft Directorate, Certification Service.
and the lever of the LH guidance unit as FAA, 10101 Hillwood Pkwy, Fort Worth, TX [FR Doc. 2017–02856 Filed 2–23–17; 8:45 am]
depicted in Detail A of Figure 5 of Eurocopter 76177; telephone (817) 222–5110; email 9-
Alert Service Bulletin EC135–67A–019, ASW-FTW-AMOC-Requests@faa.gov. BILLING CODE 4910–13–P
Revision 3, dated December 16, 2009 (EC135 (2) For operations conducted under a 14
ASB). CFR part 119 operating certificate or under
VerDate Sep<11>2014 14:13 Feb 23, 2017 Jkt 241001 PO 00000 Frm 00004 Fmt 4700 Sfmt 9990 E:\FR\FM\24FER1.SGM 24FER1](https://thefederalregister.org/doc/82_FR_11538/page/3.svg)
Document Created: 2017-02-24 01:17:19
Document Modified: 2017-02-24 01:17:19
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective March 31, 2017. | |
| 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 [email protected] | |
| FR Citation | 82 FR 11502 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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