Airworthiness Directives; Airbus Helicopters, 60349-60351 [2019-24342]

Download as PDF khammond on DSKJM1Z7X2PROD with PROPOSALS Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules attorney’s impartiality, as prohibited by 5 CFR 2635.802; or (iii) Act as an agent or attorney in any matter in which the U.S. Government is a party or has a direct and substantial interest, as prohibited by 18 U.S.C. 205. (2) Exceptions. Nothing in paragraph (c)(1) of this section prevents an attorney in the Office of the General Counsel from: (i) Acting, with or without compensation, as an agent or attorney for, or otherwise representing, the employee’s parents, spouse, child, or any other person for whom, or for any estate for which, the employee is serving as guardian, executor, administrator, trustee, or other personal fiduciary to the extent permitted by 18 U.S.C. 203(d) and 205(e), or from providing advice or counsel to such persons or estates; or (ii) Acting, without compensation, as an agent or attorney for, or otherwise representing, any person who is the subject of disciplinary, loyalty, or other personnel administration proceedings in connection with those proceedings, or from providing uncompensated advice and counsel to such person to the extent permitted by 18 U.S.C. 205; or (iii) Acting, without compensation, as an agent or attorney for, or otherwise representing any cooperative, voluntary, professional, recreational, or similar organization or group not established or operated for profit, if a majority of the organization’s or group’s members are current employees of the United States or the District of Columbia, or their spouses or dependent children. As limited by 18 U.S.C. 205(d), this exception is not permitted for any representation with respect to a matter which involves prosecuting a claim against the United States under 18 U.S.C. 205(a)(1) or (b)(1), or involves a judicial or administrative proceeding where the organization or group is a party, or involves a grant, contract, or other agreement providing for the disbursement of Federal funds to the organization or group; or (iv) Giving testimony under oath or from making statements required to be made under penalty for perjury or contempt. (3) Specific approval procedures for paragraph (c)(2) of this section. (i) The exceptions to 18 U.S.C. 203 and 205 described in paragraph (c)(2)(i) of this section do not apply unless the employee obtained the prior approval of the Government official responsible for the appointment of the employee to a Federal position. (ii) The exception to 18 U.S.C. 205 described in paragraphs (c)(2)(ii) and (iii) of this section does not apply unless VerDate Sep<11>2014 16:12 Nov 07, 2019 Jkt 250001 the employee has obtained the prior approval of a supervisory official who has authority to determine whether the employee’s proposed representation is consistent with the faithful performance of the employee’s duties. (d) Pro bono activity. Subject to compliance with paragraph (c) of this section, attorneys within the Office of the General Counsel are permitted to provide outside pro bono legal services (without compensation other than reimbursement of expenses) to organizations or individuals through a non-profit organization, without obtaining prior written approval in accordance with the procedures set forth in § 8301.102(c). Stephen Alexander Vaden, General Counsel, U.S. Department of Agriculture. In concurrence: Emory A. Rounds, III, Director, U.S. Office of Government Ethics. [FR Doc. 2019–24082 Filed 11–7–19; 8:45 am] BILLING CODE 3410–90–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0882; Product Identifier 2018–SW–113–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This proposed AD would require inspecting the attachment screws of each main gearbox (MGB) suspension bar rear attachment fitting, and depending on the outcome, applying a sealing compound, performing further inspections, and replacing affected parts. This proposed AD is prompted by reports of an elongated attachment screw and loss of tightening torque of the nut. The actions of this proposed AD are intended to address an unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by January 7, 2020. ADDRESSES: You may send comments by any of the following methods: SUMMARY: PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 60349 • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0882; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. 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. Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Comments Invited The FAA invites you to participate in this rulemaking by submitting written comments, data, or views. The FAA also invites comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, E:\FR\FM\08NOP1.SGM 08NOP1 60350 Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. The FAA will file in the docket all comments that the FAA receives, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, the FAA will consider all comments received on or before the closing date for comments. The FAA will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. The FAA may change this proposal in light of the comments received. khammond on DSKJM1Z7X2PROD with PROPOSALS Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2018– 0282, dated December 19, 2018 (EASA AD 2018–0282), to correct an unsafe condition for Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale) Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, delivered to the first owner or customer before September 1, 2018, and with attachment screws part number (P/N) 330A22013520 installed with MGB right hand (RH) side rear attachment fitting P/N 330A22270207 and left hand (LH) side rear attachment fitting P/N 330A22270206 of the MGB suspension bars. EASA advises that occurrences were reported of elongated attachment screws and loss of tightening torque of the nut installed on the affected part. EASA also advises that an investigation is ongoing to determine the root cause of this event. EASA states this condition could lead to structural failure of an MGB rear attachment fitting and possibly result in detachment of an MGB suspension bar. Accordingly, EASA AD 2018–0282 requires a one-time inspection of each attachment screw for the number of threads that protrude beyond its bolt and depending on the outcome, applying a sealing compound on the nuts, and convex and concave washers; measuring the height of the protruding threads; inspecting the tightening torque of the nuts; inspecting the upper and lower convex and concave washers; measuring and inspecting removed attachment screws; and replacing affected parts. EASA AD 2018–0282 also requires reporting information to Airbus Helicopters. EASA states EASA AD 2018–0282 is considered to be an interim action and further AD action may follow. VerDate Sep<11>2014 16:12 Nov 07, 2019 Jkt 250001 FAA’s Determination These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the European Union, EASA has notified the FAA of the unsafe condition described in its AD. The FAA is proposing this AD after evaluating all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type designs. Related Service Information Under 1 CFR Part 51 The FAA reviewed Airbus Helicopters Alert Service Bulletin No. AS332– 53.02.04, Revision 0, dated November 21, 2018 which specifies checking the number of threads that protrude beyond the bolt of the attachment screws on the RH and LH rear attachment fittings of the MGB. This service information also specifies a one-time inspection of the affected parts and depending on findings, accomplishment of applicable corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Proposed AD Requirements This proposed AD would require inspecting each screw on the RH and LH rear attachment by identifying the number of threads ‘‘F’’ that extend beyond the nut. If there are 2 or less threads on each affected part, or if there are 3 or more threads on any affected part with a thread height less than 5 mm (0.196 in), this proposed AD would require applying a sealing compound on the nuts, and convex and concave washers. If there are 3 or more threads on any affected part with a thread height of 5 mm (0.196 in) or more, this proposed AD would require removing the nut and inspecting the convex and concave washers for bent parts and corrosion. If any washers are bent or corroded, this proposed AD would require removing the washers from service. If the length ‘‘L’’ measurement of any attachment screw is greater than 59.3 mm (2.334 in), this proposed AD would require replacing the attachment fitting and the set of four screws. Differences Between This Proposed AD and the EASA AD The EASA AD requires the operator to perform a torque check and report the value to Airbus, whereas this proposed AD would not. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Interim Action The FAA considers this proposed AD interim action. The design approval holder is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, the FAA might consider additional rulemaking. Costs of Compliance The FAA estimates that this proposed AD would affect 14 helicopters of U.S. Registry. The FAA estimates that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per workhour. Inspecting the number of threads and applying a sealing compound would take about 3 work-hours for an estimated cost of $255 per helicopter and $3,570 for the U.S. fleet. Replacing an attachment fitting and the set of four screws would take about 16 work-hours and parts would cost about $6,330 for an estimated replacement cost of $7,690. 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. The FAA is 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 The FAA 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, E:\FR\FM\08NOP1.SGM 08NOP1 Federal Register / Vol. 84, No. 217 / Friday, November 8, 2019 / Proposed Rules 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. The FAA 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: Docket No. FAA–2019– 0882; Product Identifier 2018–SW–113– AD. (a) Applicability This AD applies to Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, certificated in any category, delivered to the first owner or customer before September 1, 2018, and with attachment screws part number (P/N) 330A22013520 installed with main gearbox (MGB) right hand (RH) side rear attachment fitting P/N 330A22270207 and left hand (LH) side rear attachment fitting P/N 330A22270206 of the MGB suspension bars. khammond on DSKJM1Z7X2PROD with PROPOSALS (b) Unsafe Condition This AD defines the unsafe condition as elongation of the attachment screws and loss of tightening torque of the nut. This condition could result in structural failure of an MGB attachment fitting, detachment of an MGB suspension bar, and subsequent loss of control of the helicopter. (c) Comments Due Date The FAA must receive comments by January 7, 2020. (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 110 hours time-in-service, remove the sealing compound and inspect each VerDate Sep<11>2014 16:12 Nov 07, 2019 Jkt 250001 screw on the RH and LH rear attachment fitting by identifying the number of threads ‘‘F’’ that extend beyond the nut as shown in Detail ‘‘B’’ of Figure 2 of Airbus Helicopter Alert Service Bulletin No. AS332–53.02.04, Revision 0, dated November 21, 2018 (ASB AS332–53.02.04). (1) If there are 2 or less threads on each of the four screws; or there are 3 or more threads on any screw with a thread height ‘‘H’’ less than 5 mm (0.196 in), before further flight, apply a sealing compound on the nuts, and convex and concave washers. (2) If there are 3 or more threads on any screw with a thread height ‘‘H’’ of 5 mm (0.196 in) or more, before further flight, do the following, and for more than one screw, do one at a time while working in a cross pattern: Remove from service the nut; and remove the screw from the helicopter and measure the length ‘‘L’’ of the screw as shown in Detail ‘‘D’’ of Figure 2 of ASB AS332–53.02.04. (i) If any washers are bent or corroded, before further flight, remove from service the washers. (ii) If the length ‘‘L’’ measurement is less than or equal to 59.3 mm (2.334 in) for each screw removed as required by paragraph (e)(2) of this AD, visually inspect the screw for corrosion and cracks. (A) For each screw with corrosion or a crack, before further flight, replace the screw with an airworthy screw. (B) For any screw with no corrosion or cracks, before further flight, re-install the screw and washers. Install a new nut and apply sealant. (iii) If the length ‘‘L’’ measurement is greater than 59.3 mm (2.334 in) for any screw removed as required by paragraph (e)(2) of this AD, before further flight, replace the rear attachment fitting that the screw was removed from and its set of four screws, washers, and nuts, and apply sealant as shown in Figures 2 and 3 of ASB AS332– 53.02.04. (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. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2018–0282, dated December 19, 2018. You may view the EASA AD on the internet at https://www.regulations.gov in the AD Docket. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 60351 (h) Subject Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor Gearbox. Issued in Fort Worth, Texas, on October 31, 2019. Helene T. Gandy, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2019–24342 Filed 11–7–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0859; Product Identifier 2019–NM–114–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747– 300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. This proposed AD results from fuel system reviews conducted by the manufacturer. This proposed AD would require replacement of the bonding jumpers on the auxiliary power unit (APU) fuel pump. This proposed AD would also require, for certain airplanes, installation of a second bonding jumper; an inspection of the override/jettison fuel pumps and transfer/jettison fuel pumps to determine if the bonding jumper has a one-piece braid or twopiece braid and replacement of the bonding jumper if necessary; and replacement of the bonding jumper on the electrical scavenge fuel pump. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by December 23, 2019. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– SUMMARY: E:\FR\FM\08NOP1.SGM 08NOP1

Agencies

[Federal Register Volume 84, Number 217 (Friday, November 8, 2019)]
[Proposed Rules]
[Pages 60349-60351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-24342]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0882; Product Identifier 2018-SW-113-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 
helicopters. This proposed AD would require inspecting the attachment 
screws of each main gearbox (MGB) suspension bar rear attachment 
fitting, and depending on the outcome, applying a sealing compound, 
performing further inspections, and replacing affected parts. This 
proposed AD is prompted by reports of an elongated attachment screw and 
loss of tightening torque of the nut. The actions of this proposed AD 
are intended to address an unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by January 7, 
2020.

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

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0882; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the 
economic evaluation, any comments received, and other information. The 
street address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this proposed rule, contact 
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
https://www.airbus.com/helicopters/services/technical-support.html. 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 Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting 
written comments, data, or views. The FAA also invites comments 
relating to the economic, environmental, energy, or federalism impacts 
that might result from adopting the proposals in this document. The 
most helpful comments reference a specific portion of the proposal, 
explain the reason for any recommended change, and include supporting 
data. To ensure the docket does not contain duplicate comments,

[[Page 60350]]

commenters should send only one copy of written comments, or if 
comments are filed electronically, commenters should submit only one 
time.
    The FAA will file in the docket all comments that the FAA receives, 
as well as a report summarizing each substantive public contact with 
FAA personnel concerning this proposed rulemaking. Before acting on 
this proposal, the FAA will consider all comments received on or before 
the closing date for comments. The FAA will consider comments filed 
after the comment period has closed if it is possible to do so without 
incurring expense or delay. The FAA may change this proposal in light 
of the comments received.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2018-0282, dated December 19, 
2018 (EASA AD 2018-0282), to correct an unsafe condition for Airbus 
Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale) 
Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, delivered to 
the first owner or customer before September 1, 2018, and with 
attachment screws part number (P/N) 330A22013520 installed with MGB 
right hand (RH) side rear attachment fitting P/N 330A22270207 and left 
hand (LH) side rear attachment fitting P/N 330A22270206 of the MGB 
suspension bars.
    EASA advises that occurrences were reported of elongated attachment 
screws and loss of tightening torque of the nut installed on the 
affected part. EASA also advises that an investigation is ongoing to 
determine the root cause of this event. EASA states this condition 
could lead to structural failure of an MGB rear attachment fitting and 
possibly result in detachment of an MGB suspension bar. Accordingly, 
EASA AD 2018-0282 requires a one-time inspection of each attachment 
screw for the number of threads that protrude beyond its bolt and 
depending on the outcome, applying a sealing compound on the nuts, and 
convex and concave washers; measuring the height of the protruding 
threads; inspecting the tightening torque of the nuts; inspecting the 
upper and lower convex and concave washers; measuring and inspecting 
removed attachment screws; and replacing affected parts. EASA AD 2018-
0282 also requires reporting information to Airbus Helicopters. EASA 
states EASA AD 2018-0282 is considered to be an interim action and 
further AD action may follow.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA of the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determined that an 
unsafe condition is likely to exist or develop on other products of the 
same type designs.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin No. 
AS332-53.02.04, Revision 0, dated November 21, 2018 which specifies 
checking the number of threads that protrude beyond the bolt of the 
attachment screws on the RH and LH rear attachment fittings of the MGB. 
This service information also specifies a one-time inspection of the 
affected parts and depending on findings, accomplishment of applicable 
corrective actions.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Proposed AD Requirements

    This proposed AD would require inspecting each screw on the RH and 
LH rear attachment by identifying the number of threads ``F'' that 
extend beyond the nut. If there are 2 or less threads on each affected 
part, or if there are 3 or more threads on any affected part with a 
thread height less than 5 mm (0.196 in), this proposed AD would require 
applying a sealing compound on the nuts, and convex and concave 
washers. If there are 3 or more threads on any affected part with a 
thread height of 5 mm (0.196 in) or more, this proposed AD would 
require removing the nut and inspecting the convex and concave washers 
for bent parts and corrosion. If any washers are bent or corroded, this 
proposed AD would require removing the washers from service. If the 
length ``L'' measurement of any attachment screw is greater than 59.3 
mm (2.334 in), this proposed AD would require replacing the attachment 
fitting and the set of four screws.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires the operator to perform a torque check and 
report the value to Airbus, whereas this proposed AD would not.

Interim Action

    The FAA considers this proposed AD interim action. The design 
approval holder is currently developing a modification that will 
address the unsafe condition identified in this AD. Once this 
modification is developed, approved, and available, the FAA might 
consider additional rulemaking.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 14 helicopters 
of U.S. Registry. The FAA estimates that operators may incur the 
following costs in order to comply with this AD. Labor costs are 
estimated at $85 per work-hour.
    Inspecting the number of threads and applying a sealing compound 
would take about 3 work-hours for an estimated cost of $255 per 
helicopter and $3,570 for the U.S. fleet.
    Replacing an attachment fitting and the set of four screws would 
take about 16 work-hours and parts would cost about $6,330 for an 
estimated replacement cost of $7,690.

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.
    The FAA is 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

    The FAA 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,

[[Page 60351]]

    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.
    The FAA 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: Docket No. FAA-2019-0882; Product Identifier 
2018-SW-113-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS332C, AS332C1, 
AS332L, and AS332L1 helicopters, certificated in any category, 
delivered to the first owner or customer before September 1, 2018, 
and with attachment screws part number (P/N) 330A22013520 installed 
with main gearbox (MGB) right hand (RH) side rear attachment fitting 
P/N 330A22270207 and left hand (LH) side rear attachment fitting P/N 
330A22270206 of the MGB suspension bars.

(b) Unsafe Condition

    This AD defines the unsafe condition as elongation of the 
attachment screws and loss of tightening torque of the nut. This 
condition could result in structural failure of an MGB attachment 
fitting, detachment of an MGB suspension bar, and subsequent loss of 
control of the helicopter.

(c) Comments Due Date

    The FAA must receive comments by January 7, 2020.

(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 110 hours time-in-service, remove the sealing compound 
and inspect each screw on the RH and LH rear attachment fitting by 
identifying the number of threads ``F'' that extend beyond the nut 
as shown in Detail ``B'' of Figure 2 of Airbus Helicopter Alert 
Service Bulletin No. AS332-53.02.04, Revision 0, dated November 21, 
2018 (ASB AS332-53.02.04).
    (1) If there are 2 or less threads on each of the four screws; 
or there are 3 or more threads on any screw with a thread height 
``H'' less than 5 mm (0.196 in), before further flight, apply a 
sealing compound on the nuts, and convex and concave washers.
    (2) If there are 3 or more threads on any screw with a thread 
height ``H'' of 5 mm (0.196 in) or more, before further flight, do 
the following, and for more than one screw, do one at a time while 
working in a cross pattern: Remove from service the nut; and remove 
the screw from the helicopter and measure the length ``L'' of the 
screw as shown in Detail ``D'' of Figure 2 of ASB AS332-53.02.04.
    (i) If any washers are bent or corroded, before further flight, 
remove from service the washers.
    (ii) If the length ``L'' measurement is less than or equal to 
59.3 mm (2.334 in) for each screw removed as required by paragraph 
(e)(2) of this AD, visually inspect the screw for corrosion and 
cracks.
    (A) For each screw with corrosion or a crack, before further 
flight, replace the screw with an airworthy screw.
    (B) For any screw with no corrosion or cracks, before further 
flight, re-install the screw and washers. Install a new nut and 
apply sealant.
    (iii) If the length ``L'' measurement is greater than 59.3 mm 
(2.334 in) for any screw removed as required by paragraph (e)(2) of 
this AD, before further flight, replace the rear attachment fitting 
that the screw was removed from and its set of four screws, washers, 
and nuts, and apply sealant as shown in Figures 2 and 3 of ASB 
AS332-53.02.04.

 (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, the FAA suggests 
that you notify your principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district office 
or certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2018-0282, dated December 19, 2018. You may 
view the EASA AD on the internet at https://www.regulations.gov in 
the AD Docket.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor 
Gearbox.


    Issued in Fort Worth, Texas, on October 31, 2019.
Helene T. Gandy,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2019-24342 Filed 11-7-19; 8:45 am]
 BILLING CODE 4910-13-P