Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters, 72505-72507 [2016-24860]

Download as PDF Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations compact fluorescent lamps, or integrated LED lamps. 2. Definitions: Measured initial input power means the input power to the lamp, measured after the lamp is stabilized and seasoned (if applicable), and expressed in watts (W). Measured initial lumen output means the lumen output of the lamp, measured after the lamp is stabilized and seasoned (if applicable), and expressed in lumens (lm). Power factor means the measured initial input power (watts) divided by the product of the input voltage (volts) and the input current (amps) measured at the same time as the initial input power. 3. Active Mode Test Procedures 3.1. Take measurements at full light output. 3.2. Do not use a goniophotometer. 3.3. For single base OLED and nonintegrated LED lamps, position a lamp in either the base-up and base-down orientation throughout testing. Test an equal number of lamps in the sample in the base-up and basedown orientations, except that, if the manufacturer restricts the orientation, test all of the units in the sample in the manufacturer-specified orientation. For double base OLED and non-integrated LED lamps, test all units in the horizontal orientation except that, if the manufacturer restricts the orientation, test all of the units in the sample in the manufacturer-specified orientation. 3.4. Operate the lamp at the rated voltage throughout testing. For lamps with multiple rated voltages including 120 volts, operate the lamp at 120 volts. If a lamp is not rated for 120 volts, operate the lamp at the highest 72505 rated input voltage. For non-integrated LED lamps, operate the lamp at the manufacturerdeclared input voltage and current. 3.5. Operate the lamp at the maximum input power. If multiple modes occur at the same maximum input power (such as variable CCT or CRI), the manufacturer may select any of these modes for testing; however, all measurements must be taken at the same selected mode. The manufacturer must indicate in the test report which mode was selected for testing and include detail such that another laboratory could operate the lamp in the same mode. 3.6. To measure initial lumen output, input power, input voltage, and input current use the test procedures in the table in this section. TABLE 3.1—REFERENCES TO INDUSTRY STANDARD TEST PROCEDURES Lamp type Referenced test procedure General service incandescent lamps ....................................................... Compact fluorescent lamps ...................................................................... Integrated LED lamps ............................................................................... Other incandescent lamps that are not reflector lamps ........................... Other incandescent lamps that are reflector lamps ................................. Other fluorescent lamps ........................................................................... OLED lamps ............................................................................................. Appendix R to subpart B of 10 CFR part 430. Appendix W to subpart B of 10 CFR part 430. Appendix BB to subpart B of 10 CFR part 430. IES LM–45–15, sections 4–6, and section 7.1.* IES LM–20–13, sections 4–6, and section 8.* IES LM–9–09–DD, sections 4–6, and section 7.5.* IES LM–79–08–DD, sections 1.3 (except 1.3f), 2.0, 3.0, 5.0, 7.0, 8.0, 9.1 and 9.2.* IES LM–79–08–DD, sections 1.3 (except 1.3f), 2.0, 3.0, 5.0, 7.0, 8.0, 9.1 and 9.2.* Non-integrated LED lamps ....................................................................... asabaliauskas on DSK3SPTVN1PROD with RULES * Incorporated by reference, see § 430.3. 3.7. Determine initial lamp efficacy by dividing the measured initial lumen output (lumens) by the measured initial input power (watts). 3.8. Determine power factor by dividing the measured initial input power (watts) by the product of the measured input voltage (volts) and measured input current (amps). 4. Standby Mode Test Procedure 4.1. Measure standby mode power only for lamps that are capable of standby mode operation. 4.2. Maintain lamp orientation as specified in section 3.3 of this appendix. 4.3. Connect the lamp to the manufacturerspecified wireless control network (if applicable) and configure the lamp in standby mode by sending a signal to the lamp instructing it to have zero light output. Lamp must remain connected to the network throughout testing. 4.4. Operate the lamp at the rated voltage throughout testing. For lamps with multiple rated voltages including 120 volts, operate the lamp at 120 volts. If a lamp is not rated for 120 volts, operate the lamp at the highest rated input voltage. 4.5. Stabilize the lamp prior to measurement as specified in section 5 of IEC 62301–DD (incorporated by reference; see § 430.3). 4.6. Measure the standby mode power in watts as specified in section 5 of IEC 62301– DD (incorporated by reference; see § 430.3). [FR Doc. 2016–25180 Filed 10–19–16; 8:45 am] BILLING CODE 6450–01–P VerDate Sep<11>2014 15:55 Oct 19, 2016 Jkt 241001 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. movement of the output lever in an axial direction, contact of a bolt connecting the control rod to an output lever with the actuator housing, and subsequent loss of helicopter control. DATES: This AD is effective November 25, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model MBB–BK 117 C–2 helicopters with certain duplex trim actuators installed. This AD requires repetitively inspecting the lateral and longitudinal trim actuator output levers for correct torque of the nuts. This AD was prompted by a design review that indicated the attachment screws can become loose under certain circumstances. These actions are intended to prevent the loss of an attachment screw, which could result in Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800–647–5527) is U.S. Department of Transportation, Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0578; Directorate Identifier 2013–SW–048–AD; Amendment 39–18684; AD 2016–21–03] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters AGENCY: SUMMARY: PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 E:\FR\FM\20OCR1.SGM 20OCR1 72506 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177; telephone (817) 222– 5110; email matt.wilbanks@faa.gov. SUPPLEMENTARY INFORMATION: asabaliauskas on DSK3SPTVN1PROD with RULES Discussion On August 18, 2014, at 79 FR 48696, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Model MBB–BK 117 C–2 helicopters with a lateral duplex trim actuator, part number (P/N) 418–00878–050 or P/N 418–00878–051, or a longitudinal duplex trim actuator, P/N 418–00878–000 or P/N 418–00878– 001, installed. The NPRM proposed to require repetitively inspecting the lateral and longitudinal trim actuator output levers for correct torque of the nuts. The proposed requirements were intended to prevent a loose attachment screw, which could result in movement of the output lever in an axial direction, contact of a bolt connecting the control rod to an output lever with the actuator housing, and subsequent loss of helicopter control. The NPRM was prompted by AD No. 2013–0182, dated August 12, 2013, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Helicopters Model MBB–BK 117 C–2 helicopters with a lateral duplex trim actuator, P/N 418– 00878–050 or P/N 418–00878–051, or with a longitudinal duplex trim actuator, P/N 418–00878–000 or P/N 418–00878–001. EASA advises that under unfavorable circumstances, a total loss of the trim actuator output lever attachment screw could lead to a restriction of the lateral and longitudinal control range. According to EASA, without the attachment screw, the output lever can move in the axial direction. This condition, if not detected, could cause the bolt that connects the control rod to the output lever to make contact with actuator housing, possibly resulting in reduced control of the helicopter. To prevent this condition, EASA requires an initial torque check of the lateral and longitudinal trim actuator output lever attachment screws, the application of a torque marking, and repetitive inspections for correct torque VerDate Sep<11>2014 15:55 Oct 19, 2016 Jkt 241001 thereafter. The EASA AD’s requirements are considered an interim solution, pending a terminating modification. Since the issuance of EASA AD No. 2013–0182, Eurocopter Deutschland GmbH has changed its name to Airbus Helicopters Deutschland GmbH. parts are needed, so the cost for the U.S. fleet totals $8,500. • Visually inspecting for correct torque requires 0.5 work-hour for a labor cost of about $43. No parts are needed, so the total cost for the U.S. fleet is $4,300 per inspection cycle. Comments Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on helicopters identified in this rulemaking action. We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (79 FR 48696, August 18, 2014). FAA’s Determination These helicopters have been approved by the aviation authority of Germany and are approved for operation in the United States. Pursuant to our bilateral agreement with Germany, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Interim Action We consider this AD to be an interim action because 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. Related Service Information We reviewed Eurocopter (now Airbus Helicopters) Alert Service Bulletin MBB–BK117 C–2–67A–020, Revision 0, dated June 18, 2013 (ASB), which advises of a design review that showed that a loss of the attachment screw of the trim actuator output lever could restrict the lateral and longitudinal control range. The ASB consequently calls for an initial torque check and application of torque markings of the self-locking nuts, and subsequent repetitive inspections to maintain the proper torque. Costs of Compliance We estimate that this AD affects 100 helicopters of U.S. Registry and that labor costs average $85 per work-hour. Based on these estimates, we expect the following costs: • Applying torque and torque marking to the lateral and longitudinal trim actuator output levers requires 1 work-hour for a labor cost of $85. No PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, E:\FR\FM\20OCR1.SGM 20OCR1 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ 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): ■ 2016–21–03 Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters: Amendment 39–18684; Docket No. FAA–2014–0578; Directorate Identifier 2013–SW–048–AD. (a) Applicability This AD applies to Airbus Helicopters Model MBB–BK 117 C–2 helicopters with a lateral duplex trim actuator, part number (P/ N) 418–00878–050 or P/N 418–00878–051, or a longitudinal duplex trim actuator, P/N 418– 00878–000 or P/N 418–00878–001, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as loss of a trim actuator output lever attachment screw. This condition could result in movement of the output lever in an axial direction, contact of a bolt connecting the control rod to an output lever with the actuator housing, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective November 25, 2016. asabaliauskas on DSK3SPTVN1PROD with RULES (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 300 hours time-in-service (TIS), apply a torque of 31.0 inch-pounds (3.5 Nm) to the self-locking nut (nut) on each lateral and longitudinal trim actuator output lever and apply a torque marking between the nut and the screw. (2) Thereafter at intervals not to exceed 400 hours TIS, visually inspect each nut on each lateral and longitudinal trim actuator output lever to determine whether the torque is at 31.0 inch-pounds (3.5 Nm). If the torque is not at 31.0 inch-pounds, apply a torque of 31.0 inch-pounds (3.5 Nm), remove the previous torque marking, and apply a new torque marking between the nut and the screw. (3) Do not install a lateral duplex trim actuator, part number (P/N) 418–00878–050 or P/N 418–00878–051, or a longitudinal duplex trim actuator, P/N 418–00878–000 or P/N 418–00878–001, on any helicopter unless each nut has been inspected for proper torque in accordance with the requirements of this AD. VerDate Sep<11>2014 15:55 Oct 19, 2016 Jkt 241001 (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Room 6N–321, 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) Eurocopter Alert Service Bulletin MBB– BK117 C–2–67A–020, Revision 0, dated June 18, 2013, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in the European Aviation Agency (EASA) AD No. 2013–0182, dated August 12, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2014–0578. (h) Subject Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft Flight Control. Issued in Fort Worth, Texas, on October 5, 2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–24860 Filed 10–19–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5589; Directorate Identifier 2014–NM–252–AD; Amendment 39–18678; AD 2016–20–12] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 72507 We are superseding Airworthiness Directive (AD) 2012–20– 07 for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2012–20–07 required revising the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate new limitations for fuel tank systems, and revising the maintenance program to incorporate revised fuel maintenance and inspection tasks. This new AD requires revising the maintenance or inspection program to incorporate revised fuel airworthiness limitations. This AD was prompted by Airbus issuing more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: This AD is effective November 25, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 25, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 21, 2012 (77 FR 63716, October 17, 2012). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of December 14, 2009 (74 FR 62219, November 27, 2009). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of August 28, 2007 (72 FR 40222, July 24, 2007). ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5589. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for E:\FR\FM\20OCR1.SGM 20OCR1

Agencies

[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)]
[Rules and Regulations]
[Pages 72505-72507]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24860]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0578; Directorate Identifier 2013-SW-048-AD; 
Amendment 39-18684; AD 2016-21-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
(Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Model MBB-BK 117 C-2 helicopters with certain duplex trim 
actuators installed. This AD requires repetitively inspecting the 
lateral and longitudinal trim actuator output levers for correct torque 
of the nuts. This AD was prompted by a design review that indicated the 
attachment screws can become loose under certain circumstances. These 
actions are intended to prevent the loss of an attachment screw, which 
could result in movement of the output lever in an axial direction, 
contact of a bolt connecting the control rod to an output lever with 
the actuator housing, and subsequent loss of helicopter control.

DATES: This AD is effective November 25, 2016.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, 
TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at http://www.airbushelicopters.com/techpub. You may review 
the referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort 
Worth, TX 76177.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the European Aviation Safety 
Agency (EASA) AD, the economic evaluation, any comments received, and 
other information. The street address for the Docket Operations Office 
(phone: 800-647-5527) is U.S. Department of Transportation, Docket

[[Page 72506]]

Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177; telephone 
(817) 222-5110; email matt.wilbanks@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On August 18, 2014, at 79 FR 48696, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 by adding an AD that would apply to Airbus Helicopters 
Model MBB-BK 117 C-2 helicopters with a lateral duplex trim actuator, 
part number (P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal 
duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-001, 
installed. The NPRM proposed to require repetitively inspecting the 
lateral and longitudinal trim actuator output levers for correct torque 
of the nuts. The proposed requirements were intended to prevent a loose 
attachment screw, which could result in movement of the output lever in 
an axial direction, contact of a bolt connecting the control rod to an 
output lever with the actuator housing, and subsequent loss of 
helicopter control.
    The NPRM was prompted by AD No. 2013-0182, dated August 12, 2013, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, to correct an unsafe condition for Airbus 
Helicopters Model MBB-BK 117 C-2 helicopters with a lateral duplex trim 
actuator, P/N 418-00878-050 or P/N 418-00878-051, or with a 
longitudinal duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-
001. EASA advises that under unfavorable circumstances, a total loss of 
the trim actuator output lever attachment screw could lead to a 
restriction of the lateral and longitudinal control range. According to 
EASA, without the attachment screw, the output lever can move in the 
axial direction. This condition, if not detected, could cause the bolt 
that connects the control rod to the output lever to make contact with 
actuator housing, possibly resulting in reduced control of the 
helicopter.
    To prevent this condition, EASA requires an initial torque check of 
the lateral and longitudinal trim actuator output lever attachment 
screws, the application of a torque marking, and repetitive inspections 
for correct torque thereafter. The EASA AD's requirements are 
considered an interim solution, pending a terminating modification.
    Since the issuance of EASA AD No. 2013-0182, Eurocopter Deutschland 
GmbH has changed its name to Airbus Helicopters Deutschland GmbH.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (79 FR 48696, August 
18, 2014).

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Germany and are approved for operation in the United States. Pursuant 
to our bilateral agreement with Germany, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs and that air safety and the public interest require 
adopting the AD requirements as proposed.

Interim Action

    We consider this AD to be an interim action because 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.

Related Service Information

    We reviewed Eurocopter (now Airbus Helicopters) Alert Service 
Bulletin MBB-BK117 C-2-67A-020, Revision 0, dated June 18, 2013 (ASB), 
which advises of a design review that showed that a loss of the 
attachment screw of the trim actuator output lever could restrict the 
lateral and longitudinal control range. The ASB consequently calls for 
an initial torque check and application of torque markings of the self-
locking nuts, and subsequent repetitive inspections to maintain the 
proper torque.

Costs of Compliance

    We estimate that this AD affects 100 helicopters of U.S. Registry 
and that labor costs average $85 per work-hour. Based on these 
estimates, we expect the following costs:
     Applying torque and torque marking to the lateral and 
longitudinal trim actuator output levers requires 1 work-hour for a 
labor cost of $85. No parts are needed, so the cost for the U.S. fleet 
totals $8,500.
     Visually inspecting for correct torque requires 0.5 work-
hour for a labor cost of about $43. No parts are needed, so the total 
cost for the U.S. fleet is $4,300 per inspection cycle.

Authority for This Rulemaking

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

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction; and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 72507]]

the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

    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):

2016-21-03 Airbus Helicopters Deutschland GmbH (Previously 
Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters: 
Amendment 39-18684; Docket No. FAA-2014-0578; Directorate Identifier 
2013-SW-048-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model MBB-BK 117 C-2 
helicopters with a lateral duplex trim actuator, part number (P/N) 
418-00878-050 or P/N 418-00878-051, or a longitudinal duplex trim 
actuator, P/N 418-00878-000 or P/N 418-00878-001, installed, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as loss of a trim actuator 
output lever attachment screw. This condition could result in 
movement of the output lever in an axial direction, contact of a 
bolt connecting the control rod to an output lever with the actuator 
housing, and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective November 25, 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 300 hours time-in-service (TIS), apply a torque of 
31.0 inch-pounds (3.5 Nm) to the self-locking nut (nut) on each 
lateral and longitudinal trim actuator output lever and apply a 
torque marking between the nut and the screw.
    (2) Thereafter at intervals not to exceed 400 hours TIS, 
visually inspect each nut on each lateral and longitudinal trim 
actuator output lever to determine whether the torque is at 31.0 
inch-pounds (3.5 Nm). If the torque is not at 31.0 inch-pounds, 
apply a torque of 31.0 inch-pounds (3.5 Nm), remove the previous 
torque marking, and apply a new torque marking between the nut and 
the screw.
    (3) Do not install a lateral duplex trim actuator, part number 
(P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal duplex 
trim actuator, P/N 418-00878-000 or P/N 418-00878-001, on any 
helicopter unless each nut has been inspected for proper torque in 
accordance with the requirements 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 Wilbanks, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
10101 Hillwood Pkwy., Room 6N-321, 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) Eurocopter Alert Service Bulletin MBB-BK117 C-2-67A-020, 
Revision 0, dated June 18, 2013, which is not incorporated by 
reference, contains additional information about the subject of this 
AD. For service information identified in this final rule, contact 
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at http://www.airbushelicopters.com/techpub. You may review 
a copy of the service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-321, Fort 
Worth, TX 76177.
    (2) The subject of this AD is addressed in the European Aviation 
Agency (EASA) AD No. 2013-0182, dated August 12, 2013. You may view 
the EASA AD on the Internet at http://www.regulations.gov in Docket 
No. FAA-2014-0578.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft 
Flight Control.

    Issued in Fort Worth, Texas, on October 5, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-24860 Filed 10-19-16; 8:45 am]
 BILLING CODE 4910-13-P