Airworthiness Directives; Airbus Helicopters Deutschland GmbH, 40203-40205 [2016-14470]

Download as PDF Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Proposed Rules was used, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) For cargo compartment structural parts for Model A330 airplanes: Airbus Service Bulletin A330–53–3261, including Appendixes 01, 02, and 03, dated June 23, 2015. (2) For cabin structural parts for Model A330 airplanes: Airbus Service Bulletin A330–53–3262, including Appendixes 01 and 02, dated June 23, 2015. (3) For cargo compartment structural parts for Model A340 airplanes: Airbus Service Bulletin A340–53–5072, including Appendixes 01 and 02, dated June 23, 2015. TABLE 1 TO PARAGRAPHS (g) AND (h) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED Affected part No. Acceptable replacement part No. Area F5347126620600 F5347126621000 F5347170420400 F5347170420600 F5377004320300 F5397096620200 G5367131300000 G5367173700000 G5367173800000 F5347126620000 F5347126620400 F5347170420400 F5347170420600 F5377004320051 F5397096620200 G5367131300000 G5367173700000 G5367173800000 Cabin Cabin Cargo Cargo Cargo Cargo Cargo Cargo Cargo rmajette on DSK2TPTVN1PROD with PROPOSALS (h) Replacement If during the inspection required by paragraph (g) of this AD, any affected part having a part number specified in table 1 to paragraphs (g) and (h) of this AD is found to have a measured value greater than that specified in Figure A–GFAAA, Sheet 02, ‘‘Inspection Flowchart,’’ of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Before further flight, replace with an acceptable replacement part having a part number specified in table 1 to paragraphs (g) and (h) of this AD, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using VerDate Sep<11>2014 14:42 Jun 20, 2016 Jkt 238001 any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0206, dated October 12, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–7264. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on June 9, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–14430 Filed 6–20–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 40203 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–7415; Directorate Identifier 2015–SW–076–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB–BK 117 C–2 and MBB–BK 117 D–2 helicopters. This proposed AD would require repetitive visual inspections and a one-time torque of each hydraulic module plate assembly attachment point (attachment point). This proposed AD is prompted by a design reassessment showing the current attachment point design is insufficient in preventing an attachment point failure. The proposed actions are intended to prevent failure of an attachment point, loss of the hydraulic module plate, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by August 22, 2016. 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: 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–2016– 7415; 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 E:\FR\FM\21JNP1.SGM 21JNP1 40204 Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Proposed Rules 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 the referenced 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 Group, Rotorcraft Directorate, 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. rmajette on DSK2TPTVN1PROD with PROPOSALS Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2015– 0210R1, Revision 1, dated October 28, 2015, 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 VerDate Sep<11>2014 14:42 Jun 20, 2016 Jkt 238001 helicopters. EASA advises 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 in the event one of the four single locking attachment points fails. EASA states 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 requires a repetitive inspection and one-time torque tightening of the attachment points in accordance with Airbus Helicopters’ service information. EASA considers its AD an interim action and states further AD action may follow. 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 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 and Airbus Helicopters ASB No. ASB MBB–BK117 D–2–29A–001, both Revision 0, and both dated October 12, 2015. This service information specifies a repetitive visual inspection for condition and correct installation of the attachment points, and if there is a crack, replacing the affected parts and contacting Airbus Helicopters customer support. This service information also specifies a tightening torque check after the initial inspection and, if torque cannot be applied, replacing the affected parts and contacting Airbus Helicopters customer support. 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. Proposed AD Requirements This proposed AD would require, within 100 hours time-in-service (TIS) and thereafter at intervals not to exceed 400 hours TIS, performing a visual inspection of each attachment point of PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 the hydraulic module plate assembly for a crack and proper installation. This proposed AD would also require, within 100 hours TIS, applying torque to the nuts of each attachment point. Differences Between This Proposed AD and the EASA AD The EASA AD requires contacting Airbus Helicopters customer support when replacing affected parts, and this proposed AD would not. Interim Action We consider this proposed AD to be an interim action. Airbus Helicopters is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. 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 per inspection cycle. Inspecting the torque of the four attachment points would take about 0.25 work-hour 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. 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. E:\FR\FM\21JNP1.SGM 21JNP1 Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Proposed Rules 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 adding the following new airworthiness directive (AD): ■ rmajette on DSK2TPTVN1PROD with PROPOSALS Airbus Helicopters Deutschland GmbH: Docket No. FAA–2016–7415; Directorate Identifier 2015–SW–076–AD. (a) Applicability This AD applies to Model MBB–BK 117 C– 2 and MBB–BK 117 D–2 helicopters 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 VerDate Sep<11>2014 14:42 Jun 20, 2016 Jkt 238001 hydraulic module plate and subsequent loss of control of the helicopter. (c) Comments Due Date We must receive comments by August 22, 2016. (d) Compliance (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.1.2.a. through 3.B.1.2.e., of Airbus Helicopters Alert Service Bulletin (ASB) No. ASB MBB–BK117 C–2–29A–003, Revision 0, dated October 12, 2015 (ASB MBB–BK117 C– 2–29A–003), or Airbus Helicopters ASB No. ASB MBB–BK117 D–2–29A–001, Revision 0, dated October 12, 2015 (ASB MBB–BK117 D– 2–29A–001), 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) Thereafter, at intervals not to exceed 400 hours TIS, perform the inspection in paragraph (e)(1)(i) of this AD. (f) 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 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. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015–0210R1, Revision 1, dated October 28, 2015. You may view the EASA AD on the Internet at https://www.regulations.gov in the AD Docket. (h) Subject Joint Aircraft Service Component (JASC) Code: 2900, Hydraulic Power System. Fmt 4702 [FR Doc. 2016–14470 Filed 6–20–16; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration (e) Required Actions Frm 00009 Issued in Fort Worth, Texas, on June 9, 2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. BILLING CODE 4910–13–P 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. PO 00000 40205 Sfmt 4702 14 CFR Part 39 [Docket No. FAA–2016–7261; Directorate Identifier 2016–NM–004–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–200B, 747–300, 747–400, 747–400D, and 747– 400F series airplanes. This proposed AD was prompted by a report of cracking in both the aluminum strut side skin, and corrosion resistant steel (CRES) outer spring beam support fitting. This proposed AD would require repetitive high frequency eddy current (HFEC) inspections for cracking in the strut side skin; an open-hole HFEC inspection for cracking, applicable related investigative and corrective actions; and a fastener installation modification. We are proposing this AD to detect and correct cracking of the strut side skin; such cracking could result in the failure of the outer spring beam support fitting, which could cause separation of a strut and engine from the airplane during flight. SUMMARY: We must receive comments on this proposed AD by August 5, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: E:\FR\FM\21JNP1.SGM 21JNP1

Agencies

[Federal Register Volume 81, Number 119 (Tuesday, June 21, 2016)]
[Proposed Rules]
[Pages 40203-40205]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-14470]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7415; Directorate Identifier 2015-SW-076-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 
117 C-2 and MBB-BK 117 D-2 helicopters. This proposed AD would require 
repetitive visual inspections and a one-time torque of each hydraulic 
module plate assembly attachment point (attachment point). This 
proposed AD is prompted by a design reassessment showing the current 
attachment point design is insufficient in preventing an attachment 
point failure. The proposed actions are intended to prevent failure of 
an attachment point, loss of the hydraulic module plate, and subsequent 
loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by August 22, 2016.

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-2016-
7415; 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

[[Page 40204]]

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 the referenced 
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 Group, Rotorcraft Directorate, 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

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2015-0210R1, Revision 1, dated 
October 28, 2015, 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 advises 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 in the 
event one of the four single locking attachment points fails. EASA 
states 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 requires a repetitive 
inspection and one-time torque tightening of the attachment points in 
accordance with Airbus Helicopters' service information. EASA considers 
its AD an interim action and states further AD action may follow.

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 
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 and Airbus Helicopters ASB No. ASB MBB-BK117 D-2-
29A-001, both Revision 0, and both dated October 12, 2015. This service 
information specifies a repetitive visual inspection for condition and 
correct installation of the attachment points, and if there is a crack, 
replacing the affected parts and contacting Airbus Helicopters customer 
support. This service information also specifies a tightening torque 
check after the initial inspection and, if torque cannot be applied, 
replacing the affected parts and contacting Airbus Helicopters customer 
support.
    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.

Proposed AD Requirements

    This proposed AD would require, within 100 hours time-in-service 
(TIS) and thereafter at intervals not to exceed 400 hours TIS, 
performing a visual inspection of each attachment point of the 
hydraulic module plate assembly for a crack and proper installation. 
This proposed AD would also require, within 100 hours TIS, applying 
torque to the nuts of each attachment point.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires contacting Airbus Helicopters customer support 
when replacing affected parts, and this proposed AD would not.

Interim Action

    We consider this proposed AD to be an interim action. Airbus 
Helicopters is currently developing a modification that will address 
the unsafe condition identified in this AD. Once this modification is 
developed, approved, and available, we might consider additional 
rulemaking.

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 per inspection cycle. Inspecting the torque of the 
four attachment points would take about 0.25 work-hour 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.

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.

[[Page 40205]]

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 adding the following new airworthiness 
directive (AD):

Airbus Helicopters Deutschland GmbH: Docket No. FAA-2016-7415; 
Directorate Identifier 2015-SW-076-AD.

(a) Applicability

    This AD applies to Model MBB-BK 117 C-2 and MBB-BK 117 D-2 
helicopters 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) Comments Due Date

    We must receive comments by August 22, 2016.

(d) 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.

(e) 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.1.2.a. through 3.B.1.2.e., of Airbus Helicopters 
Alert Service Bulletin (ASB) No. ASB MBB-BK117 C-2-29A-003, Revision 
0, dated October 12, 2015 (ASB MBB-BK117 C-2-29A-003), or Airbus 
Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, Revision 0, dated 
October 12, 2015 (ASB MBB-BK117 D-2-29A-001), 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) Thereafter, at intervals not to exceed 400 hours TIS, 
perform the inspection in paragraph (e)(1)(i) of this AD.

(f) 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.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2015-0210R1, Revision 1, dated October 28, 
2015. You may view the EASA AD on the Internet at https://www.regulations.gov in the AD Docket.

(h) Subject

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

    Issued in Fort Worth, Texas, on June 9, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-14470 Filed 6-20-16; 8:45 am]
BILLING CODE 4910-13-P
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