Airworthiness Directives; Airbus Helicopters Deutschland GmbH, 83182-83184 [2016-27765]

Download as PDF 83182 Federal Register / Vol. 81, No. 224 / Monday, November 21, 2016 / Proposed Rules Bulletin Number 468, dated February 17, 2016. Note 1 to paragraph (h)(1)(i) of this AD: Gulfstream GII/IIB Customer Bulletin Number 468, dated February 17, 2016, refers to Gulfstream GII Aircraft Service Change Number 300, Amendment 1, dated May 21, 1984, as an additional source of guidance for accomplishment of the rudder modification. (ii) Replace the rudder assembly with a rudder assembly that has been modified as specified in Gulfstream GII Aircraft Service Change Number 300. Do the replacement using a method approved in accordance with the procedures specified in paragraph (k)(1) of this AD. (2) For airplanes with a two-piece hinge installed: Re-identify the rudder assembly as having incorporated the actions in Gulfstream GII Aircraft Service Change Number 300, in accordance with the Accomplishment Instructions of Gulfstream GII/IIB Customer Bulletin Number 468, dated February 17, 2016. (i) Exceptions to Service Bulletin Specifications (1) Where Gulfstream GII/IIB Customer Bulletin Number 468, dated February 17, 2016, specifies to record the rudder part number and serial number on the service reply card, that action is not required by this AD. (2) Where Gulfstream GII/IIB Customer Bulletin Number 468, dated February 17, 2016, specifies to contact Gulfstream for instructions on modifying the rudder assembly, this AD requires modifying the rudder assembly before further flight using a method approved in accordance with the procedures specified in paragraph (k)(1) of this AD. comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Krista Greer, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5544; fax: 404–474–5606; email: krista.greer@faa.gov. (2) For service information identified in this AD, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@gulfstream.com; Internet http:// www.gulfstream.com/product_support/ technical_pubs/pubs/index.htm. You may view this referenced 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 November 2, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–27309 Filed 11–18–16; 8:45 am] BILLING CODE 4910–13–P asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (j) Special Flight Permit Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. DEPARTMENT OF TRANSPORTATION (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (l)(1) of this AD. (2) Before using 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. (3) Except as required by paragraph (i) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(3)(i) and (k)(3)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to [Docket No. FAA–2016–3257; Directorate Identifier 2015–SW–072–AD] VerDate Sep<11>2014 17:51 Nov 18, 2016 Jkt 241001 Federal Aviation Administration 14 CFR Part 39 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) MBB–BK 117 D–2 helicopters. This proposed AD would require repetitively inspecting the bushings of the inner and outer forward trusses of both engines. This proposed AD is prompted by reports of delaminated and worn engine mount bushings. The proposed actions are intended to detect delaminated engine mount bushings, which can lead to SUMMARY: PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 excessive vibration, cracking, failure of the engine mount front support pins, and loss of helicopter control. DATES: We must receive comments on this proposed AD by January 20, 2017. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://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 http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 3257; 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, 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 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. 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 E:\FR\FM\21NOP1.SGM 21NOP1 Federal Register / Vol. 81, No. 224 / Monday, November 21, 2016 / Proposed Rules 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. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2015– 0198, dated September 30, 2015, to correct an unsafe condition for Airbus Helicopters Model MBB–BK 117 D–2 helicopters. EASA advises that during a pre-flight check of an MBB–BK 117 D– 2 helicopter, an engine mount bushing was found delaminated. More cases of delaminated engine mount bushings were reported following additional investigations. According to EASA, this condition could lead to cracks and eventually failure of the engine mount front support pins, possibly resulting in loss of helicopter control. The EASA AD consequently requires repetitive inspections of the engine mount bushings and depending of the findings, repairing or replacing the bushings. 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 We reviewed Airbus Helicopters Alert Service Bulletin (ASB) MBB–BK117 D– VerDate Sep<11>2014 17:51 Nov 18, 2016 Jkt 241001 2–71A–002, Revision 0, dated September 28, 2015, for Model MBB–BK 117 D–2 helicopters. The ASB introduces repetitive visual inspections of the engine mount bushings for defects, deformation, separation of the rubber, and missing rubber after reports of delaminated engine mount bushings and bushings with damage to the metal inner sleeve. If there is any deformation or separation of the rubber, the ASB specifies performing a detailed inspection of the bushing in accordance with the aircraft maintenance manual. Proposed AD Requirements This proposed AD would require within 50 hours time-in-service (TIS) and at intervals not to exceed 50 hours TIS thereafter, visually inspecting the bushings of the inner and outer forward trusses of both engines, and depending on the outcome of the inspections, replacing or repairing the bushings before further flight. Differences Between This Proposed AD and the EASA AD The EASA AD allows for a 10 hour time-in-service, non-cumulative tolerance for its required compliance times. This proposed AD would not. Costs of Compliance We estimate that this proposed AD would affect 5 helicopters of U.S. Registry and that labor costs average $85 per work hour. Based on these estimates, we expect the following costs: • Inspecting the bushings would require 1 work hour. No parts would be needed, for a total cost of $85 per helicopter and $425 for the U.S. fleet. • Replacing a bushing would require 1 work hour and $373 for parts, for a total cost of $458 per bushing. 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 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 83183 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 adding the following new airworthiness directive (AD): ■ Airbus Helicopters Deutschland GmbH: Docket No. FAA–2016–3257; Directorate Identifier 2015–SW–072–AD. (a) Applicability This AD applies to Airbus Helicopters Deutschland GmbH Model MBB–BK 117 D– 2 helicopters with a bushing part number 105–60386 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a delaminated engine mount bushing. This E:\FR\FM\21NOP1.SGM 21NOP1 83184 Federal Register / Vol. 81, No. 224 / Monday, November 21, 2016 / Proposed Rules condition could result in excessive vibration, which could lead to cracking and failure of the engine mount front support pins, and loss of helicopter control. (c) Comments Due Date We must receive comments by January 20, 2017. (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 Within 50 hours time-in-service (TIS) and thereafter at intervals not to exceed 50 hours TIS: (1) Visually inspect each engine mount bushing (bushing) for separation of the rubber from the metal or missing rubber. (2) If any rubber has separated from the metal or if there is missing rubber, inspect the bushing for deformation, corrosion, and mechanical damage. (i) Replace the bushing with an airworthy bushing if there is any deformation, separation of the rubber from the metal, corrosion, or mechanical damage, or repair the bushing if the deformation, separation of the rubber, corrosion, or mechanical damage is within the maximum repair damage limitations. (ii) If the inner and outer parts of the bushing are separated with missing rubber, replace the bushing with an airworthy bushing. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (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 (1) Airbus Helicopters Alert Service Bulletin ASB MBB–BK117 D–2–71A–002, Revision 0, dated September 28, 2015, which is not incorporated by reference, contains additional information about the subject of this proposed rule. 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 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. VerDate Sep<11>2014 17:51 Nov 18, 2016 Jkt 241001 (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015–0198, dated September 30, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in the AD Docket. (h) Subject Joint Aircraft Service Component (JASC) Code: 7200, Engine (Turbine, Turboprop). Issued in Fort Worth, Texas, on November 10, 2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–27765 Filed 11–18–16; 8:45 am] BILLING CODE 4910–13–P ENVIRONMENTAL PROTECTION AGENCY 40 CFR Part 52 [EPA–R06–OAR–2015–0142; FRL–9954–66– Region 6] Approval and Promulgation of Air Quality Implementation Plans; Oklahoma; Infrastructure and Interstate Transport for the 2012 Fine Particulate Matter and Interstate Transport for the 2010 Sulfur Dioxide National Ambient Air Quality Standards Environmental Protection Agency (EPA). ACTION: Proposed rule. AGENCY: The Environmental Protection Agency (EPA) is proposing to approve and disapprove elements of State Implementation Plan (SIP) submissions from the State of Oklahoma for the 2012 Fine Particulate Matter (PM2.5) National Ambient Air Quality Standard (NAAQS or standard) and the 2010 Sulfur Dioxide (SO2) NAAQS. The 2012 PM2.5 submission addresses how the existing SIP provides for implementation, maintenance, and enforcement of this NAAQS (infrastructure SIP or i-SIP). The i-SIP ensures that the Oklahoma SIP is adequate to meet the State’s responsibilities under the Federal Clean Air Act (CAA). The majority of the 2010 SO2 submission was addressed in a separate rulemaking, only the visibility component listed in 110(a)(2)(D)(i)(II) is being addressed in this action. We are proposing to disapprove the visibility component of 110(a)(2)(D)(i)(II), often referred to as prong 4. We are also proposing to disapprove the portion of the January 28, 2015 SIP submission from Oklahoma for the 2010 Sulfur Dioxide (SO2) NAAQS only as it addresses Section 110(a)(2)(D)(i)(II) for visibility protection. SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 Written comments must be received on or before December 21, 2016. ADDRESSES: Submit your comments, identified by Docket No. EPA–R06– OAR–2015–0142, at http:// www.regulations.gov or via email to Donaldson.tracie@epa.gov. Follow the online instructions for submitting comments. Once submitted, comments cannot be edited or removed from Regulations.gov. EPA may publish any comment received to its public docket. Do not submit electronically any information you consider to be Confidential Business Information (CBI) or other information whose disclosure is restricted by statute. Multimedia submissions (audio, video, etc.) must be accompanied by a written comment. The written comment is considered the official comment and should include discussion of all points you wish to make. EPA will generally not consider comments or comment contents located outside of the primary submission (i.e. on the web, cloud, or other file sharing system). For additional submission methods, please contact Tracie Donaldson, (214) 665–6633, Donaldson.tracie@epa.gov. For the full EPA public comment policy, information about CBI or multimedia submissions, and general guidance on making effective comments, please visit http://www2.epa.gov/dockets/ commenting-epa-dockets. Docket: The docket index and publicly available docket materials for this action are available electronically at www.regulations.gov and in hard copy at EPA Region 6, 1445 Ross Avenue, Suite 700, Dallas, Texas. While all documents in the docket are listed in the index, some information may be publicly available only at the hard copy location (e.g., copyrighted material), and some may not be publicly available at either location (e.g., CBI). FOR FURTHER INFORMATION CONTACT: Tracie Donaldson, 214–665–6633, Donaldson.tracie@epa.gov. To inspect the hard copy materials, please schedule an appointment with her or Bill Deese at 214–665–7253. SUPPLEMENTARY INFORMATION: In this document ‘‘we,’’ ‘‘us,’’ and ‘‘our’’ means the EPA. DATES: I. Background On October 17, 2006, following a periodic review of the NAAQS for PM2.5, EPA revised the PM2.5 NAAQS. The 24-hour standard was revised to 35 micrograms per cubic meter (mg/m3), and the annual standard was revised to 15 mg/m3 (71 FR 61144). On December 14, 2012, we promulgated a revised E:\FR\FM\21NOP1.SGM 21NOP1

Agencies

[Federal Register Volume 81, Number 224 (Monday, November 21, 2016)]
[Proposed Rules]
[Pages 83182-83184]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-27765]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3257; Directorate Identifier 2015-SW-072-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) MBB-BK 117 D-2 
helicopters. This proposed AD would require repetitively inspecting the 
bushings of the inner and outer forward trusses of both engines. This 
proposed AD is prompted by reports of delaminated and worn engine mount 
bushings. The proposed actions are intended to detect delaminated 
engine mount bushings, which can lead to excessive vibration, cracking, 
failure of the engine mount front support pins, and loss of helicopter 
control.

DATES: We must receive comments on this proposed AD by January 20, 
2017.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://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 http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3257; 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, 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 
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.

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

[[Page 83183]]

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. 2015-0198, dated September 30, 
2015, to correct an unsafe condition for Airbus Helicopters Model MBB-
BK 117 D-2 helicopters. EASA advises that during a pre-flight check of 
an MBB-BK 117 D-2 helicopter, an engine mount bushing was found 
delaminated. More cases of delaminated engine mount bushings were 
reported following additional investigations. According to EASA, this 
condition could lead to cracks and eventually failure of the engine 
mount front support pins, possibly resulting in loss of helicopter 
control.
    The EASA AD consequently requires repetitive inspections of the 
engine mount bushings and depending of the findings, repairing or 
replacing the bushings.

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

    We reviewed Airbus Helicopters Alert Service Bulletin (ASB) MBB-
BK117 D-2-71A-002, Revision 0, dated September 28, 2015, for Model MBB-
BK 117 D-2 helicopters. The ASB introduces repetitive visual 
inspections of the engine mount bushings for defects, deformation, 
separation of the rubber, and missing rubber after reports of 
delaminated engine mount bushings and bushings with damage to the metal 
inner sleeve. If there is any deformation or separation of the rubber, 
the ASB specifies performing a detailed inspection of the bushing in 
accordance with the aircraft maintenance manual.

Proposed AD Requirements

    This proposed AD would require within 50 hours time-in-service 
(TIS) and at intervals not to exceed 50 hours TIS thereafter, visually 
inspecting the bushings of the inner and outer forward trusses of both 
engines, and depending on the outcome of the inspections, replacing or 
repairing the bushings before further flight.

Differences Between This Proposed AD and the EASA AD

    The EASA AD allows for a 10 hour time-in-service, non-cumulative 
tolerance for its required compliance times. This proposed AD would 
not.

Costs of Compliance

    We estimate that this proposed AD would affect 5 helicopters of 
U.S. Registry and that labor costs average $85 per work hour. Based on 
these estimates, we expect the following costs:
     Inspecting the bushings would require 1 work hour. No 
parts would be needed, for a total cost of $85 per helicopter and $425 
for the U.S. fleet.
     Replacing a bushing would require 1 work hour and $373 for 
parts, for a total cost of $458 per bushing.

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 adding the following new airworthiness 
directive (AD):

Airbus Helicopters Deutschland GmbH: Docket No. FAA-2016-3257; 
Directorate Identifier 2015-SW-072-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH Model 
MBB-BK 117 D-2 helicopters with a bushing part number 105-60386 
installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a delaminated engine 
mount bushing. This

[[Page 83184]]

condition could result in excessive vibration, which could lead to 
cracking and failure of the engine mount front support pins, and 
loss of helicopter control.

(c) Comments Due Date

    We must receive comments by January 20, 2017.

(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

    Within 50 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 50 hours TIS:
    (1) Visually inspect each engine mount bushing (bushing) for 
separation of the rubber from the metal or missing rubber.
    (2) If any rubber has separated from the metal or if there is 
missing rubber, inspect the bushing for deformation, corrosion, and 
mechanical damage.
    (i) Replace the bushing with an airworthy bushing if there is 
any deformation, separation of the rubber from the metal, corrosion, 
or mechanical damage, or repair the bushing if the deformation, 
separation of the rubber, corrosion, or mechanical damage is within 
the maximum repair damage limitations.
    (ii) If the inner and outer parts of the bushing are separated 
with missing rubber, replace the bushing with an airworthy bushing.

(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

    (1) Airbus Helicopters Alert Service Bulletin ASB MBB-BK117 D-2-
71A-002, Revision 0, dated September 28, 2015, which is not 
incorporated by reference, contains additional information about the 
subject of this proposed rule. 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 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.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2015-0198, dated September 30, 2015. You 
may view the EASA AD on the Internet at http://www.regulations.gov 
in the AD Docket.

 (h) Subject

    Joint Aircraft Service Component (JASC) Code: 7200, Engine 
(Turbine, Turboprop).

    Issued in Fort Worth, Texas, on November 10, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-27765 Filed 11-18-16; 8:45 am]
 BILLING CODE 4910-13-P