Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 57390-57392 [2017-26039]

Download as PDF 57390 Federal Register / Vol. 82, No. 232 / Tuesday, December 5, 2017 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1123; Product Identifier 2017–SW–013–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2017–02– 07 for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB–BK 117 C–2 and Model MBB–BK 117 D–2 helicopters. AD 2017–02–07 currently requires a repetitive inspection and a one-time torque of each hydraulic module plate assembly attachment point (attachment point). Since we issued AD 2017–02–07, a terminating action has been developed to address the unsafe condition. This proposed AD would retain the initial inspection and torque requirements of AD 2017–02–07 and require replacing the attachment point hardware. The actions of this proposed AD are intended to prevent an unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 5, 2018. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: sradovich on DSK3GMQ082PROD with PROPOSALS 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–2017– 1123; 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 proposed AD, the VerDate Sep<11>2014 18:01 Dec 04, 2017 Jkt 244001 European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbushelicopters.com/techpub. You may review service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion We issued AD 2017–02–07, Amendment 39–18786 (82 FR 10267, February 10, 2017) (2017–02–07) for Airbus Helicopters Model MBB–BK 117 C–2 helicopters, serial numbers up to PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 and including 9750, and Model MBB– BK 117 D–2 helicopters, serial numbers up to and including 20110, with a hydraulic module plate assembly part number B291M0003103 with a single locking attachment point installed. AD 2017–02–07 requires a repetitive inspection and a one-time torque of the attachment points. The actions in AD 2017–02–07 are intended to prevent failure of an attachment point, loss of the hydraulic module plate, and subsequent loss of control of the helicopter. EASA, which is the Technical Agent for the Member States of the European Union, issued EASA AD No. 2015– 0210R1, Revision 1, dated October 28, 2015 (2015–0210R1), to correct an unsafe condition for Airbus Helicopters Model MBB–BK117 C–2, MBB–BK117 C–2e, MBB–BK117 D–2, and MBB– BK117 D–2m helicopters. EASA advised that the hydraulic plate assembly on certain MBB–BK117 models has four attachment points on the fuselage secured by a single locking mechanism. According to EASA, a design reassessment revealed stiffness of the hydraulic plate may be insufficient to withstand the in-service loads in the event one of the four single locking attachment points fails. EASA stated that if this condition is not detected and corrected, it may lead to loss of the hydraulic module plate and possible loss of control of the helicopter. Therefore, the EASA AD required a repetitive inspection and one-time torque tightening of the attachment points in accordance with Airbus Helicopters’ service information. EASA considered its AD an interim action and stated further AD action may follow. EASA subsequently revised AD 2015–0210R1 and issued AD No. 2015– 0210R2, dated December 2, 2016 (2015– 0210R2), to exclude from the applicability helicopters with an improved double locking attachment mechanism that is not subject to the unsafe condition. Actions Since AD 2017–02–07 Was Issued Since we issued AD 2017–02–07, Airbus Helicopters revised its service information to add procedures to modify single locking attachment mechanisms to double locking attachment mechanisms. EASA subsequently superseded AD 2015– 0210R2 with AD No. 2017–0047, dated March 13, 2017, to require installation of double locking attachments. FAA’s Determination These helicopters have been approved by the aviation authority of Germany E:\FR\FM\05DEP1.SGM 05DEP1 Federal Register / Vol. 82, No. 232 / Tuesday, December 5, 2017 / Proposed Rules 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 its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB– BK117 C–2–29A–003 for Model MBB– BK 117 C–2 helicopters and ASB No. ASB MBB–BK117 D–2–29A–001 for Model MBB–BK 117 D–2 helicopters, both Revision 2 and both dated February 1, 2017. Until the attachment points are modified with double locking attachment mechanisms, this service information specifies a repetitive visual inspection for condition and correct installation of the attachment points and replacing the affected parts if there is a crack. This service information also specifies a tightening torque check after the initial inspection and replacing the affected parts if torque cannot be applied. This revision of the service information also specifies procedures to replace the single locking attachment hardware with double locking attachment hardware. 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. sradovich on DSK3GMQ082PROD with PROPOSALS Other Related Service Information We also reviewed Airbus Helicopters ASB No. ASB MBB–BK117 C–2–29A– 003 for Model MBB–BK 117 C–2 helicopters and ASB No. ASB MBB– BK117 D–2–29A–001 for Model MBB– BK 117 D–2 helicopters, both Revision 1 and both dated October 14, 2016. Revision 1 of this service information contains the same visual inspection and torque tightening check procedures as Revision 2. However, Revision 2 of this service information adds the procedures to replace the single locking attachment hardware with double locking attachment hardware. Proposed AD Requirements This proposed AD would require, within 100 hours time-in-service (TIS), unless already done within the last 100 hours TIS, performing a visual inspection of each attachment point of the hydraulic module plate assembly for a crack and proper installation, and applying torque to the nuts of each VerDate Sep<11>2014 18:01 Dec 04, 2017 Jkt 244001 attachment point. This proposed AD would also require, within 300 hours TIS, replacing each single locking attachment point mechanism with a double locking attachment point mechanism. Differences Between This Proposed AD and the EASA AD The EASA AD specifies performing the visual inspection of each attachment point at intervals not exceeding 400 flight hours. This proposed AD would not require a repetitive inspection. This proposed AD would require the replacement of each single locking attachment point mechanism with a double locking attachment point mechanism within 300 hours TIS instead, which would make subsequent inspections unnecessary. Costs of Compliance We estimate that this proposed AD would affect 134 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. We estimate the cost of labor at $85 per work-hour. Visually inspecting the four attachment points would take about 0.75 work-hour for an estimated cost of $64 per helicopter and $8,576 for the U.S. fleet. Inspecting the torque of the four attachment points would take about 0.25 work-hour for an estimated cost of $21 per helicopter and $2,814 for the U.S. fleet. Replacing any of the attachment point parts would take a minimal amount of time and parts would cost about $48 per attachment point. Installing four double locking attachment point mechanisms would take a minimal amount of time and parts would cost about $400 per helicopter and $53,600 for the U.S. fleet. According to Airbus Helicopters service information, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage by Airbus Helicopters. Accordingly, we have included all costs in our cost estimate. 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 57391 promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska 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 proposed 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2017–02–07, Amendment 39–18786 (82 FR 10267, February 10, 2017), and adding the following new AD: ■ Airbus Helicopters Deutschland GmbH: Docket No. FAA–2017–1123; Product Identifier 2017–SW–013–AD. E:\FR\FM\05DEP1.SGM 05DEP1 57392 Federal Register / Vol. 82, No. 232 / Tuesday, December 5, 2017 / Proposed Rules (a) Applicability This AD applies to Model MBB–BK 117 C– 2 helicopters, serial numbers up to and including 9750, and Model MBB–BK 117 D– 2 helicopters, serial numbers up to and including 20110, with a hydraulic module plate assembly part number B291M0003103 with a single locking attachment point installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as failure of a hydraulic module plate assembly attachment point (attachment point). This condition could result in loss of the hydraulic module plate and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes 2017–02–07, Amendment 39–18786 (82 FR 10267, February 10, 2017). (d) Comments Due Date We must receive comments by February 5, 2018. sradovich on DSK3GMQ082PROD with PROPOSALS (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) Within 100 hours time-in-service (TIS): (i) Visually inspect the split pins, castellated nuts, plugs, nuts, and hexagon bolts of each attachment point for a crack and for proper installation by following the Accomplishment Instructions, paragraphs 3.B.1.3.a. through 3.B.1.3.d., of Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB–BK117 C–2–29A–003 (ASB MBB– BK117 C–2–29A–003) or Airbus Helicopters ASB No. ASB MBB–BK117 D–2–29A–001 (ASB MBB–BK117 D–2–29A–001), both Revision 2 and both dated February 1, 2017, as applicable to your model helicopter. Replace any part that has a crack before further flight. If the split pins, castellated nuts, or hexagon bolts are not as depicted in Figure 2 of ASB MBB–BK117 C–2–29A–003 or ASB MBB–BK117 D–2–29A–001, before further flight, properly install them. (ii) Apply a torque of 9 to 10 Nm to the left-hand and right-hand nuts of each attachment point. If a torque of 9 to 10 Nm cannot be applied, replace the affected nut before further flight. (2) Within 300 hours TIS: (i) Replace each forward single locking attachment hardware with double locking attachment hardware by following the Accomplishment Instructions, paragraphs 3.B.3.3. through 3.B.3.6. on page 11 of ASB MBB–BK117 C–2–29A–003 or ASB MBB– BK117 D–2–29A–001, as applicable to your model helicopter, except you are not required to discard old parts. (ii) Replace each aft single locking attachment hardware with double locking attachment hardware by following the Accomplishment Instructions, paragraphs 3.B.3.1. through 3.B.3.3. on page 13 of ASB MBB–BK117 C–2–29A–003 or ASB MBB– BK117 D–2–29A–001, as applicable to your VerDate Sep<11>2014 18:01 Dec 04, 2017 Jkt 244001 model helicopter, except you are not required to discard old parts. DEPARTMENT OF THE TREASURY (g) Credit for Previous Actions Alcohol and Tobacco Tax and Trade Bureau Actions accomplished before the effective date of this AD in accordance with the procedures specified in AD 2017–02–07, Amendment 39–18786 (82 FR 10267, February 10, 2017) or Airbus Helicopters ASB No. ASB MBB–BK117 C–2–29A–003 or ASB No. ASB MBB–BK117 D–2–29A–001, both Revision 1 and both dated October 14, 2016, are considered acceptable for compliance with the corresponding actions specified in paragraph (f)(1) of this AD. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASW-FTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (i) Additional Information (1) Airbus Helicopters ASB No. ASB MBB– BK117 C–2–29A–003 and ASB No. ASB MBB–BK117 D–2–29A–001, both Revision 1 and both dated October 14, 2016, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2017–0047, dated March 13, 2017. You may view the EASA AD on the Internet at https://www.regulations.gov in the AD Docket. (j) Subject Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic Power System. Issued in Fort Worth, Texas, on November 17, 2017. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2017–26039 Filed 12–4–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 27 CFR Parts 24 and 27 [Docket No. TTB–2016–0014; Notice No. 168A; Re: Notice No. 168, T.D. TTB–147, and T.D. TTB 147A] RIN 1513–AC31 Implementation of Statutory Amendments Requiring the Modification of the Definition of Hard Cider; Delayed Compliance Date for the Hard Cider Tax Class Labeling Statement Requirement; Reopening of Comment Period Alcohol and Tobacco Tax and Trade Bureau, Treasury. ACTION: Notice of proposed rulemaking and reopening of comment period. AGENCY: On January 23, 2017, the Alcohol and Tobacco Tax and Trade Bureau (TTB) published a temporary rule, T.D. TTB–147, Implementation of Statutory Amendments Requiring the Modification of the Definition of Hard Cider, that amended its regulations to implement changes made to the definition of ‘‘hard cider’’ in the Internal Revenue Code of 1986 by the Protecting Americans from Tax Hikes Act (PATH Act) of 2015. The amended regulations included a requirement that the statement ‘‘Tax class 5041(b)(6)’’ appear on the container of any wine for which the hard cider tax rate is claimed if the wine is removed from wine premises or customs custody on or after January 1, 2018. Concurrent with the temporary rule, TTB published Notice of Proposed Rulemaking No. 168 requesting comments on the regulatory amendments made by T.D. TTB–147. In response to a comment received from a cider industry trade association, TTB, in a temporary rule published elsewhere in this issue of the Federal Register, is now delaying the compliance date for the hard cider tax class labeling requirement by one year, until January 1, 2019. In this document, TTB is requesting comments on that delayed compliance date, and we are also reopening the comment period for Notice No. 168 for an additional 60 days to request comments on the regulatory amendments described in T.D. TTB– 147. SUMMARY: Comments on the delayed compliance date referenced in this document (Notice No. 168A) are due on or before February 5, 2018. The comment period for the proposed rule, Notice No. 168, published on January DATES: E:\FR\FM\05DEP1.SGM 05DEP1

Agencies

[Federal Register Volume 82, Number 232 (Tuesday, December 5, 2017)]
[Proposed Rules]
[Pages 57390-57392]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26039]



[[Page 57390]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1123; Product Identifier 2017-SW-013-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2017-02-
07 for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model 
MBB-BK 117 C-2 and Model MBB-BK 117 D-2 helicopters. AD 2017-02-07 
currently requires a repetitive inspection and a one-time torque of 
each hydraulic module plate assembly attachment point (attachment 
point). Since we issued AD 2017-02-07, a terminating action has been 
developed to address the unsafe condition. This proposed AD would 
retain the initial inspection and torque requirements of AD 2017-02-07 
and require replacing the attachment point hardware. The actions of 
this proposed AD are intended to prevent an unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by February 5, 
2018.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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-2017-
1123; 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 proposed AD, the European Aviation Safety Agency (EASA) 
AD, the economic evaluation, any comments received and other 
information. The street address for the Docket Operations Office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this proposed rule, contact 
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
https://www.airbushelicopters.com/techpub. You may review service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email matthew.fuller@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    We issued AD 2017-02-07, Amendment 39-18786 (82 FR 10267, February 
10, 2017) (2017-02-07) for Airbus Helicopters Model MBB-BK 117 C-2 
helicopters, serial numbers up to and including 9750, and Model MBB-BK 
117 D-2 helicopters, serial numbers up to and including 20110, with a 
hydraulic module plate assembly part number B291M0003103 with a single 
locking attachment point installed. AD 2017-02-07 requires a repetitive 
inspection and a one-time torque of the attachment points. The actions 
in AD 2017-02-07 are intended to prevent failure of an attachment 
point, loss of the hydraulic module plate, and subsequent loss of 
control of the helicopter.
    EASA, which is the Technical Agent for the Member States of the 
European Union, issued EASA AD No. 2015-0210R1, Revision 1, dated 
October 28, 2015 (2015-0210R1), to correct an unsafe condition for 
Airbus Helicopters Model MBB-BK117 C-2, MBB-BK117 C-2e, MBB-BK117 D-2, 
and MBB-BK117 D-2m helicopters. EASA advised that the hydraulic plate 
assembly on certain MBB-BK117 models has four attachment points on the 
fuselage secured by a single locking mechanism. According to EASA, a 
design reassessment revealed stiffness of the hydraulic plate may be 
insufficient to withstand the in-service loads in the event one of the 
four single locking attachment points fails. EASA stated that if this 
condition is not detected and corrected, it may lead to loss of the 
hydraulic module plate and possible loss of control of the helicopter. 
Therefore, the EASA AD required a repetitive inspection and one-time 
torque tightening of the attachment points in accordance with Airbus 
Helicopters' service information.
    EASA considered its AD an interim action and stated further AD 
action may follow. EASA subsequently revised AD 2015-0210R1 and issued 
AD No. 2015-0210R2, dated December 2, 2016 (2015-0210R2), to exclude 
from the applicability helicopters with an improved double locking 
attachment mechanism that is not subject to the unsafe condition.

Actions Since AD 2017-02-07 Was Issued

    Since we issued AD 2017-02-07, Airbus Helicopters revised its 
service information to add procedures to modify single locking 
attachment mechanisms to double locking attachment mechanisms. EASA 
subsequently superseded AD 2015-0210R2 with AD No. 2017-0047, dated 
March 13, 2017, to require installation of double locking attachments.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Germany

[[Page 57391]]

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 its AD. We are 
proposing this AD because we evaluated all known relevant information 
and determined that an unsafe condition is likely to exist or develop 
on other products of the same type design.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. ASB 
MBB-BK117 C-2-29A-003 for Model MBB-BK 117 C-2 helicopters and ASB No. 
ASB MBB-BK117 D-2-29A-001 for Model MBB-BK 117 D-2 helicopters, both 
Revision 2 and both dated February 1, 2017. Until the attachment points 
are modified with double locking attachment mechanisms, this service 
information specifies a repetitive visual inspection for condition and 
correct installation of the attachment points and replacing the 
affected parts if there is a crack. This service information also 
specifies a tightening torque check after the initial inspection and 
replacing the affected parts if torque cannot be applied. This revision 
of the service information also specifies procedures to replace the 
single locking attachment hardware with double locking attachment 
hardware.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Other Related Service Information

    We also reviewed Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-
003 for Model MBB-BK 117 C-2 helicopters and ASB No. ASB MBB-BK117 D-2-
29A-001 for Model MBB-BK 117 D-2 helicopters, both Revision 1 and both 
dated October 14, 2016. Revision 1 of this service information contains 
the same visual inspection and torque tightening check procedures as 
Revision 2. However, Revision 2 of this service information adds the 
procedures to replace the single locking attachment hardware with 
double locking attachment hardware.

Proposed AD Requirements

    This proposed AD would require, within 100 hours time-in-service 
(TIS), unless already done within the last 100 hours TIS, performing a 
visual inspection of each attachment point of the hydraulic module 
plate assembly for a crack and proper installation, and applying torque 
to the nuts of each attachment point. This proposed AD would also 
require, within 300 hours TIS, replacing each single locking attachment 
point mechanism with a double locking attachment point mechanism.

Differences Between This Proposed AD and the EASA AD

    The EASA AD specifies performing the visual inspection of each 
attachment point at intervals not exceeding 400 flight hours. This 
proposed AD would not require a repetitive inspection. This proposed AD 
would require the replacement of each single locking attachment point 
mechanism with a double locking attachment point mechanism within 300 
hours TIS instead, which would make subsequent inspections unnecessary.

Costs of Compliance

    We estimate that this proposed AD would affect 134 helicopters of 
U.S. Registry. We estimate that operators may incur the following costs 
in order to comply with this AD. We estimate the cost of labor at $85 
per work-hour. Visually inspecting the four attachment points would 
take about 0.75 work-hour for an estimated cost of $64 per helicopter 
and $8,576 for the U.S. fleet. Inspecting the torque of the four 
attachment points would take about 0.25 work-hour for an estimated cost 
of $21 per helicopter and $2,814 for the U.S. fleet. Replacing any of 
the attachment point parts would take a minimal amount of time and 
parts would cost about $48 per attachment point. Installing four double 
locking attachment point mechanisms would take a minimal amount of time 
and parts would cost about $400 per helicopter and $53,600 for the U.S. 
fleet.
    According to Airbus Helicopters service information, some of the 
costs of this proposed AD may be covered under warranty, thereby 
reducing the cost impact on affected individuals. We do not control 
warranty coverage by Airbus Helicopters. Accordingly, we have included 
all costs in our cost estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

    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) 
2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017), and 
adding the following new AD:

Airbus Helicopters Deutschland GmbH: Docket No. FAA-2017-1123; 
Product Identifier 2017-SW-013-AD.

[[Page 57392]]

(a) Applicability

    This AD applies to Model MBB-BK 117 C-2 helicopters, serial 
numbers up to and including 9750, and Model MBB-BK 117 D-2 
helicopters, serial numbers up to and including 20110, with a 
hydraulic module plate assembly part number B291M0003103 with a 
single locking attachment point installed, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a hydraulic 
module plate assembly attachment point (attachment point). This 
condition could result in loss of the hydraulic module plate and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes 2017-02-07, Amendment 39-18786 (82 FR 10267, 
February 10, 2017).

(d) Comments Due Date

    We must receive comments by February 5, 2018.

(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) Within 100 hours time-in-service (TIS):
    (i) Visually inspect the split pins, castellated nuts, plugs, 
nuts, and hexagon bolts of each attachment point for a crack and for 
proper installation by following the Accomplishment Instructions, 
paragraphs 3.B.1.3.a. through 3.B.1.3.d., of Airbus Helicopters 
Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-
BK117 C-2-29A-003) or Airbus Helicopters ASB No. ASB MBB-BK117 D-2-
29A-001 (ASB MBB-BK117 D-2-29A-001), both Revision 2 and both dated 
February 1, 2017, as applicable to your model helicopter. Replace 
any part that has a crack before further flight. If the split pins, 
castellated nuts, or hexagon bolts are not as depicted in Figure 2 
of ASB MBB-BK117 C-2-29A-003 or ASB MBB-BK117 D-2-29A-001, before 
further flight, properly install them.
    (ii) Apply a torque of 9 to 10 Nm to the left-hand and right-
hand nuts of each attachment point. If a torque of 9 to 10 Nm cannot 
be applied, replace the affected nut before further flight.
    (2) Within 300 hours TIS:
    (i) Replace each forward single locking attachment hardware with 
double locking attachment hardware by following the Accomplishment 
Instructions, paragraphs 3.B.3.3. through 3.B.3.6. on page 11 of ASB 
MBB-BK117 C-2-29A-003 or ASB MBB-BK117 D-2-29A-001, as applicable to 
your model helicopter, except you are not required to discard old 
parts.
    (ii) Replace each aft single locking attachment hardware with 
double locking attachment hardware by following the Accomplishment 
Instructions, paragraphs 3.B.3.1. through 3.B.3.3. on page 13 of ASB 
MBB-BK117 C-2-29A-003 or ASB MBB-BK117 D-2-29A-001, as applicable to 
your model helicopter, except you are not required to discard old 
parts.

(g) Credit for Previous Actions

    Actions accomplished before the effective date of this AD in 
accordance with the procedures specified in AD 2017-02-07, Amendment 
39-18786 (82 FR 10267, February 10, 2017) or Airbus Helicopters ASB 
No. ASB MBB-BK117 C-2-29A-003 or ASB No. ASB MBB-BK117 D-2-29A-001, 
both Revision 1 and both dated October 14, 2016, are considered 
acceptable for compliance with the corresponding actions specified 
in paragraph (f)(1) of this AD.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, FAA, may approve 
AMOCs for this AD. Send your proposal to: Matt Fuller, Senior 
Aviation Safety Engineer, Safety Management Section, Rotorcraft 
Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone (817) 222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(i) Additional Information

    (1) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 and ASB 
No. ASB MBB-BK117 D-2-29A-001, both Revision 1 and both dated 
October 14, 2016, which are not incorporated by reference, contain 
additional information about the subject of this AD. For service 
information identified in this AD, contact Airbus Helicopters, 2701 
N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or 
(800) 232-0323; fax (972) 641-3775; or at https://www.airbushelicopters.com/techpub. You may review a copy of the 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 
76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2017-0047, dated March 13, 2017. You may 
view the EASA AD on the Internet at https://www.regulations.gov in 
the AD Docket.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic 
Power System.

    Issued in Fort Worth, Texas, on November 17, 2017.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2017-26039 Filed 12-4-17; 8:45 am]
 BILLING CODE 4910-13-P