Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters, 30864-30866 [2019-13604]

Download as PDF 30864 Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Rules and Regulations Dated: June 4, 2019. Bruce Summers, Administrator, Agricultural Marketing Service. [FR Doc. 2019–12019 Filed 6–27–19; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0980; Product Identifier 2017–SW–123–AD; Amendment 39–19669; AD 2019–12–14] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB–BK 117 C–2 helicopters. This AD requires establishing or reducing the life limit of various parts. This AD was prompted by recalculations. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective August 2, 2019. ADDRESSES: For service information identified in this final 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.helicopters.airbus.com/website/ en/ref/Technical-Support_73.html. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. khammond on DSKBBV9HB2PROD with RULES 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–2018– 0980; or in person at Docket Operations 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 Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room VerDate Sep<11>2014 16:17 Jun 27, 2019 Jkt 247001 W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On November 19, 2018 at 83 FR 58191, 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 certain parts installed. The NPRM proposed to require establishing and reducing the life limit of the following parts: Main rotor head—nut, upper and lower quadruple nut, bolts, and inner sleeve; swash plate control ring assembly; rotor flight control collective bellcrank-K; cyclic control rod tube; and upper control forked lever. The proposed requirements were intended to prevent a part remaining in service beyond its fatigue life, which could result in failure of a part and loss of control of the helicopter. The NPRM was prompted by EASA AD No. 2017–0174, dated September 12, 2017 (EASA AD 2017–0174), 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. EASA advises that recalculation by Airbus Helicopters has resulted in new or reduced life limits for certain parts. EASA AD 2017–0174 states the life limits are mandatory for continued airworthiness and failing to replace life-limited parts as specified could result in an unsafe condition. To address this condition, EASA AD 2017– 0174 requires replacing the affected parts before exceeding their new or reduced life limit. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM. FAA’s Determination These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to our bilateral agreement with the European Union, EASA has notified us of the unsafe condition described in its AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 condition exists and is likely to exist or develop on other products of the same type designs and that air safety and the public interest require adopting the AD requirements as proposed except for minor editorial changes. ‘‘Bellcrank-K (collective) (4)’’ was listed in Table 1 to paragraph (e) of this AD, but should have been ‘‘Bellcrank-K (collective)’’ instead. The cost of the parts listed in the Costs of Compliance section have also been updated to reflect current market prices. The updated costs are considered non-substantial. These minor editorial changes are consistent with the intent of the proposals in the NPRM and will not increase the economic burden on any operator nor increase the scope of this AD. Related Service Information We reviewed Airbus Helicopters Alert Service Bulletin ASB MBB–BK117 C–2– 04A–008, Revision 0, dated April 27, 2017, for Model MBB–BK 117 C–2 and C–2e helicopters. This service information specifies entering into the helicopter records the reduced and new airworthiness life limits for certain partnumbered main rotor head, swash plate, rotor flight controls, cyclic controls, and upper controls parts. Costs of Compliance We estimate that this AD affects 128 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Labor costs average $85 per work-hour. Replacing a nut takes about 5 workhours and parts cost about $3,736 for an estimated replacement cost of $4,161. Replacing a quadruple nut upper takes about 5 work-hours and parts cost about $3,682 for an estimated replacement cost of $4,107. Replacing a quadruple nut lower takes about 5 work-hours and parts cost about $3,819 for an estimated replacement cost of $4,244. Replacing a bolt takes about 2 workhours and parts cost about $418 for an estimated replacement cost of $588. Replacing an inner sleeve takes about 2 work-hours and parts cost about $20,826 for an estimated replacement cost of $20,996. Replacing a control ring assembly takes about 5 work-hours and parts cost about $11,500 for an estimated replacement cost of $11,925. Replacing a bellcrank-K (collective) takes about 4 work-hours and parts cost about $3,400 for an estimated replacement cost of $3,740. Replacing a control rod tube takes about 4 work-hours and parts cost about $1,197 for an estimated replacement cost of $1,537. E:\FR\FM\28JNR1.SGM 28JNR1 Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Rules and Regulations Replacing a forked lever takes about 3 work-hours and parts cost about $6,138 for an estimated replacement cost of $6,393. 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) Will not affect intrastate aviation in Alaska, and (3) 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 19669; Docket No. FAA–2018–0980; Product Identifier 2017–SW–123–AD. (a) Applicability This AD applies to Airbus Helicopters Deutschland GmbH Model MBB–BK 117 C– 2 helicopters with a part listed in Table 1 to paragraph (e) of this AD installed, certificated in any category. Note 1 to paragraph (a) of this AD: Helicopters with an MBB–BK117 C–2e designation are Model MBB–BK117 C–2 helicopters. (b) Unsafe Condition This AD defines the unsafe condition as a part remaining in service beyond its fatigue life. This condition could result in failure of a part and loss of control of the helicopter. (c) Effective Date This AD becomes effective August 2, 2019. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES (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. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 30865 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–12–14 Airbus Helicopters Deutschland GmbH: Amendment 39– Before further flight, remove from service any part that has reached or exceeded its new or reduced life limit as listed in Table 1 to paragraph (e) of this AD. Thereafter, remove from service each part on or before reaching its new or reduced life limit as listed in Table 1 to paragraph (e) of this AD. For purposes of this AD, a ‘‘landing’’ is counted any time the helicopter lifts off into the air and then lands again regardless of the duration of the landing and regardless of whether the engine is shut down. TABLE 1 TO PARAGRAPH (e) Part name Part No. (P/N) Life limit Nut ............................................. B622M1003201 ................................................ Quadruple nut upper ................. Quadruple nut lower ................. Bolt ............................................ B622M1004201 ................................................ B622M1005201 ................................................ B622M1006201, B622M1007201 .................... Inner sleeve .............................. Control ring assembly ............... Bellcrank-K (collective) ............. Control rod tube ........................ Forked lever .............................. B622M1009201 B623M2001101 B670M7021201 B291M1015201 B671M7007201 B671M7007205 65,800 landings or 10,123 hours time-in-service (TIS) if the number of landings is unknown. 60,000 landings or 9,230 hours TIS if the number of landings is unknown. 31,200 landings or 4,800 hours TIS if the number of landings is unknown. 13,300 hours TIS. 27,600 hours TIS. 21,500 hours TIS. 30,000 hours TIS. 22,500 Hours TIS. khammond on DSKBBV9HB2PROD with RULES (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. VerDate Sep<11>2014 16:17 Jun 27, 2019 Jkt 247001 ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ (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 C–2–04A–008, PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Revision 0, dated April 27, 2017, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.helicopters.airbus.com/website/en/ref/ Technical-Support_73.html. You may review the referenced service information at the FAA, Office of the Regional Counsel, E:\FR\FM\28JNR1.SGM 28JNR1 30866 Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Rules and Regulations Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2017–0174, dated September 12, 2017. You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA–2018–0980. (h) Subject Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor Head; 6230 Main Rotor Mast/Swashplate; and 6710, Main Rotor Control. Issued in Fort Worth, Texas, on June 18, 2019. James A. Grigg, Acting Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2019–13604 Filed 6–27–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0648; Product Identifier 2017–SW–087–AD; Amendment 39–19670; AD 2019–12–15] RIN 2120–AA64 Airworthiness Directives; Leonardo S.p.A. Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Leonardo S.p.A. (Leonardo) Model AB139 and AW139 helicopters. This AD requires replacing screws installed on the left and right main landing gear (MLG) shock absorber assembly. This AD was prompted by a report that some screws may have been manufactured without meeting specifications. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 2, 2019. SUMMARY: For service information identified in this final rule, contact Leonardo S.p.A. Helicopters, Matteo Ragazzi, Head of Airworthiness, Viale G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone +39– 0331–711756; fax +39–0331–229046; or at https://www.leonardocompany.com/-/ bulletins. 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. khammond on DSKBBV9HB2PROD with RULES ADDRESSES: VerDate Sep<11>2014 16:17 Jun 27, 2019 Jkt 247001 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–2018– 0648; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the European Aviation Safety Agency (EASA) AD, the regulatory evaluation, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email david.hatfield@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Leonardo S.p.A. Model AB139 and AW139 helicopters. The NPRM published in the Federal Register on July 19, 2018 (83 FR 34072). The NPRM was prompted by a report that some screws may have been manufactured without meeting specifications. The NPRM proposed to require replacing screws installed on the left and right MLG shock absorber assembly. We are issuing this AD to address an MLG shock absorber screw that does not meet specifications. This condition could result in failure of the MLG shock absorber, collapse or retraction of the MLG, and subsequent damage to the helicopter. EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2016– 0077, dated April 19, 2016, to correct an unsafe condition for Finmeccanica S.p.A. (previously Agusta) Model AB139 and AW139 helicopters if equipped with kit ‘‘Increased Gross Weight 6800 kg’’ part number (P/N) 4G0000F00111 (kit). EASA advises of a manufacturing issue with the standard screws (P/N NAS1351–5H12P) installed on MLG shock absorber assembly P/N 1652B0000–01. According to EASA, a material analysis shows that the MLG shock absorber screws may have a lower fatigue life than the screws used during the certification fatigue tests. EASA states the affected MLG units have been PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 identified by serial number (S/N). EASA also advises that this unsafe condition, if not detected and corrected, could result in failure of the MLG shock absorber, collapse or retraction of the MLG, and subsequent damage to the helicopter and injury to occupants. To correct this condition, the EASA AD requires replacing each standard screw with a new screw P/N 1652A0001–01 and re-identifying the S/ N of each MLG shock absorber assembly that has the new screw installed, and prohibits installing any affected MLG shock absorber assembly unless the screw has been replaced. Comments We gave the public the opportunity to participate in developing this final rule, but we did not receive any comments on the NPRM. FAA’s Determination These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to our bilateral agreement with the European Union, EASA 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 except for a minor editorial change to meet current publishing requirements. In the Required Actions paragraph, instances of ‘‘Figure 1 to paragraph (a)’’ have been changed to ‘‘Figure 1 to paragraphs (a) and (e)(2).’’ This minor editorial change is consistent with the intent of the proposals in the NPRM and will not increase the economic burden on any operator nor increase the scope of this AD. Related Service Information We reviewed Finmeccanica Bollettino Tecnico No. 139–397, dated April 7, 2016, which contains procedures for replacing the standard screws installed on the left and right MLG assembly and for re-identifying the MLG shock absorber assembly P/N and the MLG assembly S/N. Costs of Compliance We estimate that this AD affects 111 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD, based on an average labor rate of $85 per work-hour. Replacing the screws on the left and right MLG assemblies requires about 16 E:\FR\FM\28JNR1.SGM 28JNR1

Agencies

[Federal Register Volume 84, Number 125 (Friday, June 28, 2019)]
[Rules and Regulations]
[Pages 30864-30866]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13604]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0980; Product Identifier 2017-SW-123-AD; Amendment 
39-19669; AD 2019-12-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 
helicopters. This AD requires establishing or reducing the life limit 
of various parts. This AD was prompted by recalculations. The actions 
of this AD are intended to address an unsafe condition on these 
products.

DATES: This AD is effective August 2, 2019.

ADDRESSES: For service information identified in this final 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.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review a copy of 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0980; or in person at Docket Operations 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 Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    On November 19, 2018 at 83 FR 58191, 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 certain parts installed. The NPRM 
proposed to require establishing and reducing the life limit of the 
following parts: Main rotor head--nut, upper and lower quadruple nut, 
bolts, and inner sleeve; swash plate control ring assembly; rotor 
flight control collective bellcrank-K; cyclic control rod tube; and 
upper control forked lever. The proposed requirements were intended to 
prevent a part remaining in service beyond its fatigue life, which 
could result in failure of a part and loss of control of the 
helicopter.
    The NPRM was prompted by EASA AD No. 2017-0174, dated September 12, 
2017 (EASA AD 2017-0174), 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. EASA 
advises that recalculation by Airbus Helicopters has resulted in new or 
reduced life limits for certain parts. EASA AD 2017-0174 states the 
life limits are mandatory for continued airworthiness and failing to 
replace life-limited parts as specified could result in an unsafe 
condition. To address this condition, EASA AD 2017-0174 requires 
replacing the affected parts before exceeding their new or reduced life 
limit.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to our bilateral agreement 
with the European Union, EASA has notified us of the unsafe condition 
described in its 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 products of the same type 
designs and that air safety and the public interest require adopting 
the AD requirements as proposed except for minor editorial changes. 
``Bellcrank-K (collective) (4)'' was listed in Table 1 to paragraph (e) 
of this AD, but should have been ``Bellcrank-K (collective)'' instead. 
The cost of the parts listed in the Costs of Compliance section have 
also been updated to reflect current market prices. The updated costs 
are considered non-substantial. These minor editorial changes are 
consistent with the intent of the proposals in the NPRM and will not 
increase the economic burden on any operator nor increase the scope of 
this AD.

Related Service Information

    We reviewed Airbus Helicopters Alert Service Bulletin ASB MBB-BK117 
C-2-04A-008, Revision 0, dated April 27, 2017, for Model MBB-BK 117 C-2 
and C-2e helicopters. This service information specifies entering into 
the helicopter records the reduced and new airworthiness life limits 
for certain part-numbered main rotor head, swash plate, rotor flight 
controls, cyclic controls, and upper controls parts.

Costs of Compliance

    We estimate that this AD affects 128 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. Labor costs average $85 per work-hour.
    Replacing a nut takes about 5 work-hours and parts cost about 
$3,736 for an estimated replacement cost of $4,161.
    Replacing a quadruple nut upper takes about 5 work-hours and parts 
cost about $3,682 for an estimated replacement cost of $4,107.
    Replacing a quadruple nut lower takes about 5 work-hours and parts 
cost about $3,819 for an estimated replacement cost of $4,244.
    Replacing a bolt takes about 2 work-hours and parts cost about $418 
for an estimated replacement cost of $588.
    Replacing an inner sleeve takes about 2 work-hours and parts cost 
about $20,826 for an estimated replacement cost of $20,996.
    Replacing a control ring assembly takes about 5 work-hours and 
parts cost about $11,500 for an estimated replacement cost of $11,925.
    Replacing a bellcrank-K (collective) takes about 4 work-hours and 
parts cost about $3,400 for an estimated replacement cost of $3,740.
    Replacing a control rod tube takes about 4 work-hours and parts 
cost about $1,197 for an estimated replacement cost of $1,537.

[[Page 30865]]

    Replacing a forked lever takes about 3 work-hours and parts cost 
about $6,138 for an estimated replacement cost of $6,393.

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) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

    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):

2019-12-14 Airbus Helicopters Deutschland GmbH: Amendment 39-19669; 
Docket No. FAA-2018-0980; Product Identifier 2017-SW-123-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH Model 
MBB-BK 117 C-2 helicopters with a part listed in Table 1 to 
paragraph (e) of this AD installed, certificated in any category.

    Note 1 to paragraph (a) of this AD: Helicopters with an MBB-
BK117 C-2e designation are Model MBB-BK117 C-2 helicopters.

(b) Unsafe Condition

    This AD defines the unsafe condition as a part remaining in 
service beyond its fatigue life. This condition could result in 
failure of a part and loss of control of the helicopter.

 (c) Effective Date

    This AD becomes effective August 2, 2019.

(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

    Before further flight, remove from service any part that has 
reached or exceeded its new or reduced life limit as listed in Table 
1 to paragraph (e) of this AD. Thereafter, remove from service each 
part on or before reaching its new or reduced life limit as listed 
in Table 1 to paragraph (e) of this AD. For purposes of this AD, a 
``landing'' is counted any time the helicopter lifts off into the 
air and then lands again regardless of the duration of the landing 
and regardless of whether the engine is shut down.

                        Table 1 to Paragraph (e)
------------------------------------------------------------------------
           Part name              Part No. (P/N)         Life limit
------------------------------------------------------------------------
Nut...........................  B622M1003201.....  65,800 landings or
                                                    10,123 hours time-in-
                                                    service (TIS) if the
                                                    number of landings
                                                    is unknown.
Quadruple nut upper...........  B622M1004201.....  60,000 landings or
Quadruple nut lower...........  B622M1005201.....   9,230 hours TIS if
                                                    the number of
                                                    landings is unknown.
Bolt..........................  B622M1006201,      31,200 landings or
                                 B622M1007201.      4,800 hours TIS if
                                                    the number of
                                                    landings is unknown.
Inner sleeve..................  B622M1009201.....  13,300 hours TIS.
Control ring assembly.........  B623M2001101.....  27,600 hours TIS.
Bellcrank-K (collective)......  B670M7021201.....  21,500 hours TIS.
Control rod tube..............  B291M1015201.....  30,000 hours TIS.
Forked lever..................  B671M7007201.....  22,500 Hours TIS.
                                B671M7007205.....
------------------------------------------------------------------------

(f) Alternative Methods of Compliance (AMOCs)

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

(g) Additional Information

    (1) Airbus Helicopters Alert Service Bulletin ASB MBB-BK117 C-2-
04A-008, Revision 0, dated April 27, 2017, which is not incorporated 
by reference, contains additional information about the subject of 
this AD. For service information identified in this AD, contact 
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or 
at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review the referenced service information 
at the FAA, Office of the Regional Counsel,

[[Page 30866]]

Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 
76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2017-0174, dated September 12, 2017. You 
may view the EASA AD on the internet at https://www.regulations.gov 
in Docket No. FAA-2018-0980.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor 
Head; 6230 Main Rotor Mast/Swashplate; and 6710, Main Rotor Control.

    Issued in Fort Worth, Texas, on June 18, 2019.
James A. Grigg,
Acting Deputy Director for Regulatory Operations, Compliance & 
Airworthiness Division, Aircraft Certification Service.
[FR Doc. 2019-13604 Filed 6-27-19; 8:45 am]
 BILLING CODE 4910-13-P
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