83 FR 10360 - Airworthiness Directives; Airbus Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 47 (March 9, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 47 (March 9, 2018)
| Page Range | 10360-10363 | |
| FR Document | 2018-04647 |
[Federal Register Volume 83, Number 47 (Friday, March 9, 2018)] [Rules and Regulations] [Pages 10360-10363] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-04647] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0177; Product Identifier 2017-SW-138-AD; Amendment 39-19218; AD 2018-05-09] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires inspecting the tail rotor (T/R) flapping hinge link (hinge) and reporting the results. This AD is prompted by a report of a damaged flapping hinge link. The actions of this AD are intended to prevent an unsafe condition on these products. DATES: This AD becomes effective March 26, 2018. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of March 26, 2018. We must receive comments on this AD by May 8, 2018. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the [[Page 10361]] online instructions for sending your comments electronically. Fax: 202-493-2251. Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001. Hand Delivery: Deliver to the ``Mail'' address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0177; 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, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for Docket Operations (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this 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 http://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, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0177. FOR FURTHER INFORMATION CONTACT: Martin R. Crane, Aviation Safety Engineer, Regulations & Policy Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222- 5110; email [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued Emergency AD No. 2017-0232-E, dated November 21, 2017, to correct an unsafe condition for Airbus Helicopters Model AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters. The EASA AD was prompted by the in-flight failure of a pin in a hinge attaching the T/R. EASA advises that damage to the hinge on a T/R blade was reported and that an investigation is ongoing to determine the root cause of the damage. EASA further advises that this condition could lead to failure of the hinge, unbalance of the T/R, and detachment of the T/R gearbox and hub with subsequent loss of control of the helicopter. To correct this unsafe condition, the EASA AD requires a one-time inspection of the flapping hinges, and depending on the findings, corrective actions. It also requires reporting the findings and sending any cracked components to Airbus Helicopters to support the investigation. FAA's Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, 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. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 64.00.43, Revision 0, dated November 21, 2017, for Model AS332-series helicopters. This service information describes procedures for visually and dye penetrant inspecting the hinges of all five T/Rs. 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. AD Requirements This AD requires, within 25 hours time-in-service (TIS): Performing a tactile inspection of each hinge for friction points; Measuring for play in the drag plane; Measuring the tightening torque of each spindle bolt. [cir] If the tightening torque is not within the minimum and maximum torque, dye-penetrant inspecting the spindle bolt for a crack and removing the spindle bolt and hexagonal castellated nut from service; [cir] If the tightening torque is within the minimum and maximum torque, inspecting the spindle bolt for corrosion and fretting. Inspecting the bearing race inner ring and bearing needles for spalling and replacing the bearing race if there is any spalling; Measuring the thickness of each stop washer and removing the stop washer from service if the thickness is less than 1.5 mm (.060 inch); and Inspecting the inner ring for brinelling. [cir] If there is brinelling deeper than 0.1 mm (.004 inch), repairing the hinge. [cir] If there is brinelling 0.1 mm (.004 inch) or less, dye- penetrant inspecting the inner ring for a crack. This AD also requires, within 10 days after the inspection, reporting the results of each inspection and measurement to Airbus Helicopters. Differences Between This AD and the EASA AD The EASA AD requires compliance within 25 hours TIS or at the next 50 hour inspection of the T/R, whichever is later; this AD requires compliance within 25 hours TIS. The EASA AD requires returning parts to Airbus Helicopters, and this AD does not. Interim Action We considered this AD interim action. The inspection reports that are required by this AD will enable Airbus Helicopters to obtain better insight into the cause of the damaged flapping hinge link, and eventually develop final action to address the unsafe condition. Once [[Page 10362]] final action has been identified, we might consider further rulemaking. Costs of Compliance We estimate that this AD affects 20 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per hour, inspecting 5 T/R hinges will require 8 hours, and required materials cost would be minimal, for a cost per helicopter of $680 and a cost of $13,600 to the U.S. fleet. Reporting the inspection findings would require about 30 minutes, for a cost per helicopter of $43 and a cost of $860 to the U.S. fleet. If required, dye-penetrant inspecting the spindle bolt or inner ring would require about 1 hour, and required materials cost would be minimal, for a cost per helicopter of $85. If required, replacing a spindle bolt would require about 1 hour, and required parts would cost $625, for a cost per helicopter of $710. If required, replacing the bearing race would require about 1 hour, and required parts would cost $585, for a cost per helicopter of $670. If required, replacing the inner ring would require about 1 hour, and required parts would cost $1,986, for a cost per helicopter of $2,071. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting required by this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave, SW, Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES-200. FAA's Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the inspections required by this AD must be accomplished within 25 hours TIS, a relatively short period of time for these helicopters as they are primarily used for offshore operations. Therefore, we find good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reason stated above, we find that good cause exists for making this amendment effective in less than 30 days. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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, 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, 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): 2018-05-09 Airbus Helicopters: Amendment 39-19218; Docket No. FAA- 2018-0177; Product Identifier 2017-SW-138-AD. (a) Applicability This AD applies to Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as failure of a tail rotor (T/R) flapping hinge link (hinge). This condition could result in unbalance of the T/R, detachment of the T/R gearbox and hub, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective March 26, 2018. (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 25 hours time-in-service, inspect each T/R hinge as follows: (i) Point each T/R blade downward and perform a tactile inspection of each hinge for friction points. Record whether there is a friction point. (ii) Measure play in the drag plane depicted as ``J'' in Figure 1 of Airbus Helicopters Emergency Alert Service Bulletin No. 64.00.43, Revision 0, dated November 21, 2017 (EASB 64.00.43), and record the measurement. (iii) Measure the tightening torque of each spindle bolt and record the measurement. (A) If the tightening torque is less than 564 inch-pounds or more than 955 inch-pounds, before further flight, dye-penetrant inspect the spindle bolt for a crack and record whether there is a crack. Remove the spindle bolt and the hexagonal castellated nut from service. (B) If the tightening torque is between 564 inch-pounds and 955 inch-pounds, inspect [[Page 10363]] the spindle bolt for corrosion and fretting and record whether there is corrosion or fretting. If there is corrosion or fretting that cannot be removed by hand with an abrasive pad, before further flight, dye-penetrant inspect the spindle bolt for a crack in areas Z1 and Z2 as depicted in Figure 2 of EASB 64.00.43. If there is a crack, before further flight, record that there is a crack and remove from service the spindle bolt, hexagonal castellated nut, inner ring, stop washers, needle bearings or set of needle bearings, seals, and split washer. (iv) Remove the inner ring and stop washers. (v) Inspect the bearing race inner ring and bearing needles for spalling. If there is any spalling, before further flight, record that there is spalling and replace the bearing race. (vi) Measure the thickness of each stop washer. If the thickness is less than 1.5 mm (.060 inch), before further flight, remove the stop washer from service. Record that the stop washer was removed from service because of thickness. (vii) Inspect the inner ring for brinelling. (A) If there is brinelling more than 0.1 mm (.004 inch) in depth, before further flight, record that there is brinelling and repair the hinge. (B) If there is brinelling 0.1 mm (.004 inch) or less in depth, before further flight, turn the inner ring to position the area with brinelling on the T/R hub pin side. Record the brinelling and the turning of the inner ring. Dye-penetrant inspect the inner ring for a crack in the area depicted as ``Z3'' of Figure 3 of EASB 64.00.43. If there is a crack, before further flight, record that there is a crack in the inner ring and remove from service the spindle bolt, hexagonal castellated nut, inner ring, stop washers, needle bearings or set of needle bearings, seals, and split washer. (2) Within 10 days after the inspection, submit a report of the measurements and findings of the inspection required by paragraph (e)(1) of this AD, as specified in the Appendix of EASB 64.00.43, to [email protected]. (f) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 30 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (g) 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: Martin R. Crane, Aviation Safety Engineer, Regulations & Policy 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. (h) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) Emergency AD No. 2017-0232-E, dated November 21, 2017. You may view the EASA AD on the internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2018-0177. (i) Subject Joint Aircraft Service Component (JASC) Code: 6420 Tail Rotor Head. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 64.00.43, Revision 0, dated November 21, 2017. (ii) Reserved. Note 1 to paragraph (j)(2): Airbus Helicopters EASB No. 64.00.43, Revision 0, dated November 21, 2017, is co-published as one document along with Airbus Helicopters EASB No. 64.00.21, Revision 0, dated November 21, 2017, which is not incorporated by reference. (3) For Airbus Helicopters 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 http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N- 321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Fort Worth, Texas, on February 26, 2018. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2018-04647 Filed 3-8-18; 8:45 am] BILLING CODE 4910-13-P
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PART 39—AIRWORTHINESS Alert Operators Transmission A26N003–16 Office—EIAS, 1 Rond Point Maurice
DIRECTIVES because the torque values were incorrect. Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
(h) Other FAA AD Provisions 93 44 51; email account.airworth-eas@
■ 1. The authority citation for part 39
The following provisions also apply to this airbus.com; internet http://www.airbus.com.
continues to read as follows: AD: (4) You may view this service information
Authority: 49 U.S.C. 106(g), 40113, 44701. (1) Alternative Methods of Compliance at the FAA, Transport Standards Branch,
(AMOCs): The Manager, International 2200 South 216th St., Des Moines, WA. For
§ 39.13 [Amended] Section, Transport Standards Branch, FAA, information on the availability of this
■ 2. The FAA amends § 39.13 by adding has the authority to approve AMOCs for this material at the FAA, call 206–231–3195.
the following new airworthiness AD, if requested using the procedures found (5) You may view this service information
in 14 CFR 39.19. In accordance with 14 CFR that is incorporated by reference at the
directive (AD):
39.19, send your request to your principal National Archives and Records
2018–05–11 Airbus: Amendment 39–19220; inspector or local Flight Standards District Administration (NARA). For information on
Docket No. FAA–2018–0164; Product Office, as appropriate. If sending information the availability of this material at NARA, call
Identifier 2018–NM–026–AD. directly to the International Section, send it 202–741–6030, or go to: http://
to the attention of the person identified in www.archives.gov/federal-register/cfr/ibr-
(a) Effective Date
paragraph (j)(2) of this AD. Information may locations.html.
This AD becomes effective March 26, 2018. be emailed to: 9-ANM-116-AMOC-
REQUESTS@faa.gov. Before using any Issued in Renton, Washington, on February
(b) Affected ADs 28, 2018.
approved AMOC, notify your appropriate
None. principal inspector, or lacking a principal Michael Kaszycki,
(c) Applicability inspector, the manager of the local flight Acting Director, System Oversight Division,
standards district office/certificate holding Aircraft Certification Service.
This AD applies to Airbus Model A320– district office.
214, –251N, and –271N airplanes, certificated [FR Doc. 2018–04646 Filed 3–8–18; 8:45 am]
(2) Contacting the Manufacturer: For any
in any category, having manufacturer serial requirement in this AD to obtain corrective BILLING CODE 4910–13–P
numbers 07126, 07141, 07189, 07200, 07221, actions from a manufacturer, the action must
07226, 07235, 07245, 07251, 07256, 07264, be accomplished using a method approved
07272, 07279, 07319, 07337 and 07340. by the Manager, International Section, DEPARTMENT OF TRANSPORTATION
(d) Subject Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or Federal Aviation Administration
Air Transport Association (ATA) of Airbus’s EASA Design Organization
America Code 26, Fire Protection. Approval (DOA). If approved by the DOA, 14 CFR Part 39
(e) Reason the approval must include the DOA-
authorized signature. [Docket No. FAA–2018–0177; Product
This AD was prompted by a report that a
dynamometric key, previously used for Identifier 2017–SW–138–AD; Amendment
(i) Special Flight Permits
installing the cargo fire extinguishing bottle 39–19218; AD 2018–05–09]
Special flight permits, as described in
system, was out of tolerance. As a result, an Section 21.197 and Section 21.199 of the RIN 2120–AA64
incorrect torque value may have been applied Federal Aviation Regulations (14 CFR 21.197
to the bolts maintaining the fire and 21.199), may be issued to operate the Airworthiness Directives; Airbus
extinguishing bottle in place. We are issuing airplane to a location where the requirements
this AD to detect and correct damaged bolts
Helicopters
of this AD can be accomplished, provided no
in the cargo fire extinguishing bottle system, cargo is in the lower deck of the cargo AGENCY: Federal Aviation
which could lead to disconnection of a cargo compartment. Administration (FAA), Department of
fire extinguishing bottle, possibly resulting in
loss of the fire protection system in the lower (j) Related Information Transportation (DOT).
deck cargo compartment. (1) Refer to Mandatory Continuing ACTION: Final rule; request for
Airworthiness Information (MCAI) EASA comments.
(f) Compliance
Airworthiness Directive 2018–0038, dated
Comply with this AD within the February 7, 2018, for related information. SUMMARY: We are adopting a new
compliance times specified, unless already You may examine the MCAI on the internet airworthiness directive (AD) for Airbus
done. at http://www.regulations.gov by searching Helicopters Model AS332C, AS332C1,
(g) Inspection and Corrective Actions for and locating Docket No. FAA–2018–0164. AS332L, and AS332L1 helicopters. This
(2) For more information about this AD, AD requires inspecting the tail rotor (T/
Within 30 days after the effective date of contact Sanjay Ralhan, Aerospace Engineer,
this AD: Do a general visual inspection for R) flapping hinge link (hinge) and
International Section, Transport Standards
any damaged bolt and nut in each cargo fire Branch, FAA, 2200 South 216th St., Des
reporting the results. This AD is
extinguishing bottle installation in Moines, WA 98198; telephone and fax 206– prompted by a report of a damaged
accordance with the instructions in Airbus 231–3223. flapping hinge link. The actions of this
Alert Operators Transmission A26N003–16, AD are intended to prevent an unsafe
Revision 01, dated June 12, 2017. (k) Material Incorporated by Reference
condition on these products.
(1) If any damaged bolt or nut is detected, (1) The Director of the Federal Register
DATES: This AD becomes effective
before further flight, replace all damaged approved the incorporation by reference
bolts and nuts, in accordance with the (IBR) of the service information listed in this March 26, 2018.
instructions in Airbus Alert Operators paragraph under 5 U.S.C. 552(a) and 1 CFR The Director of the Federal Register
Transmission A26N003–16, Revision 01, part 51. approved the incorporation by reference
dated June 12, 2017. (2) You must use this service information of a certain document listed in this AD
(2) If no damage is detected, before further as applicable to do the actions required by as of March 26, 2018.
amozie on DSK30RV082PROD with RULES
flight, reinstall the bolts and nuts, in this AD, unless this AD specifies otherwise. We must receive comments on this
accordance with the instructions in Airbus (i) Airbus Alert Operators Transmission AD by May 8, 2018.
Alert Operators Transmission A26N003–16, A26N003–16, Revision 01, dated June 12,
Revision 01, dated June 12, 2017. 2017. ADDRESSES: You may send comments by
Note 1 to paragraph (g) of this AD: No (ii) Reserved. any of the following methods:
credit will be provided for accomplishment (3) For service information identified in • Federal eRulemaking Docket: Go to
of the actions in the original issue of Airbus this AD, contact Airbus, Airworthiness http://www.regulations.gov. Follow the
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final action has been identified, we and comment prior to adoption of this List of Subjects in 14 CFR Part 39
might consider further rulemaking. rule because the inspections required by Air transportation, Aircraft, Aviation
this AD must be accomplished within safety, Incorporation by reference,
Costs of Compliance
25 hours TIS, a relatively short period Safety.
We estimate that this AD affects 20 of time for these helicopters as they are
helicopters of U.S. Registry. primarily used for offshore operations. Adoption of the Amendment
We estimate that operators may incur Therefore, we find good cause that Accordingly, under the authority
the following costs in order to comply notice and opportunity for prior public delegated to me by the Administrator,
with this AD. At an average labor rate comment are impracticable. the FAA amends 14 CFR part 39 as
of $85 per hour, inspecting 5 T/R hinges In addition, for the reason stated follows:
will require 8 hours, and required above, we find that good cause exists for
materials cost would be minimal, for a making this amendment effective in less PART 39—AIRWORTHINESS
cost per helicopter of $680 and a cost of than 30 days. DIRECTIVES
$13,600 to the U.S. fleet. Reporting the
inspection findings would require about Authority for This Rulemaking ■ 1. The authority citation for part 39
30 minutes, for a cost per helicopter of continues to read as follows:
Title 49 of the United States Code
$43 and a cost of $860 to the U.S. fleet. specifies the FAA’s authority to issue Authority: 49 U.S.C. 106(g), 40113, 44701.
If required, dye-penetrant inspecting the rules on aviation safety. Subtitle I,
spindle bolt or inner ring would require § 39.13 [Amended]
section 106, describes the authority of
about 1 hour, and required materials the FAA Administrator. ‘‘Subtitle VII: ■ 2. The FAA amends § 39.13 by adding
cost would be minimal, for a cost per Aviation Programs,’’ describes in more the following new airworthiness
helicopter of $85. If required, replacing detail the scope of the Agency’s directive (AD):
a spindle bolt would require about 1 authority. 2018–05–09 Airbus Helicopters:
hour, and required parts would cost Amendment 39–19218; Docket No.
$625, for a cost per helicopter of $710. We are issuing this rulemaking under
FAA–2018–0177; Product Identifier
If required, replacing the bearing race the authority described in ‘‘Subtitle VII,
2017–SW–138–AD.
would require about 1 hour, and Part A, Subpart III, Section 44701:
General requirements.’’ Under that (a) Applicability
required parts would cost $585, for a
cost per helicopter of $670. section, Congress charges the FAA with This AD applies to Airbus Helicopters
If required, replacing the inner ring promoting safe flight of civil aircraft in Model AS332C, AS332C1, AS332L, and
air commerce by prescribing regulations AS332L1 helicopters, certificated in any
would require about 1 hour, and
for practices, methods, and procedures category.
required parts would cost $1,986, for a
cost per helicopter of $2,071. the Administrator finds necessary for (b) Unsafe Condition
safety in air commerce. This regulation This AD defines the unsafe condition as
Paperwork Reduction Act is within the scope of that authority failure of a tail rotor (T/R) flapping hinge link
A federal agency may not conduct or because it addresses an unsafe condition (hinge). This condition could result in
sponsor, and a person is not required to that is likely to exist or develop on unbalance of the T/R, detachment of the T/
respond to, nor shall a person be subject products identified in this rulemaking R gearbox and hub, and subsequent loss of
to penalty for failure to comply with a action. control of the helicopter.
collection of information subject to the Regulatory Findings (c) Effective Date
requirements of the Paperwork This AD becomes effective March 26, 2018.
Reduction Act unless that collection of We determined that this AD will not
information displays a current valid have federalism implications under (d) Compliance
OMB control number. The control Executive Order 13132. This AD will You are responsible for performing each
number for the collection of information not have a substantial direct effect on action required by this AD within the
required by this AD is 2120–0056. The the States, on the relationship between specified compliance time unless it has
already been accomplished prior to that time.
paperwork cost associated with this AD the national Government and the States,
has been detailed in the Costs of or on the distribution of power and (e) Required Actions
Compliance section of this document responsibilities among the various (1) Within 25 hours time-in-service,
and includes time for reviewing levels of government. inspect each T/R hinge as follows:
instructions, as well as completing and For the reasons discussed, I certify (i) Point each T/R blade downward and
reviewing the collection of information. that this AD: perform a tactile inspection of each hinge for
Therefore, all reporting required by this friction points. Record whether there is a
1. Is not a ‘‘significant regulatory friction point.
AD is mandatory. Comments concerning action’’ under Executive Order 12866; (ii) Measure play in the drag plane
the accuracy of this burden and 2. Is not a ‘‘significant rule’’ under depicted as ‘‘J’’ in Figure 1 of Airbus
suggestions for reducing the burden DOT Regulatory Policies and Procedures Helicopters Emergency Alert Service Bulletin
should be directed to the FAA at 800 (44 FR 11034, February 26, 1979); No. 64.00.43, Revision 0, dated November 21,
Independence Ave, SW, Washington, 2017 (EASB 64.00.43), and record the
3. Will not affect intrastate aviation in measurement.
DC 20591. ATTN: Information
Alaska to the extent that it justifies (iii) Measure the tightening torque of each
Collection Clearance Officer, AES–200.
making a regulatory distinction; and spindle bolt and record the measurement.
FAA’s Justification and Determination 4. Will not have a significant (A) If the tightening torque is less than 564
of the Effective Date economic impact, positive or negative, inch-pounds or more than 955 inch-pounds,
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on a substantial number of small entities before further flight, dye-penetrant inspect
An unsafe condition exists that
under the criteria of the Regulatory the spindle bolt for a crack and record
requires the immediate adoption of this whether there is a crack. Remove the spindle
AD without providing an opportunity Flexibility Act. bolt and the hexagonal castellated nut from
for public comments prior to adoption. We prepared an economic evaluation service.
The FAA has found that the risk to the of the estimated costs to comply with (B) If the tightening torque is between 564
flying public justifies waiving notice this AD and placed it in the AD docket. inch-pounds and 955 inch-pounds, inspect
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![Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Rules and Regulations 10363
the spindle bolt for corrosion and fretting and (g) Alternative Methods of Compliance Issued in Fort Worth, Texas, on February
record whether there is corrosion or fretting. (AMOCs) 26, 2018.
If there is corrosion or fretting that cannot be (1) The Manager, Safety Management Lance T. Gant,
removed by hand with an abrasive pad, Section, Rotorcraft Standards Branch, FAA, Director, Compliance & Airworthiness
before further flight, dye-penetrant inspect may approve AMOCs for this AD. Send your Division, Aircraft Certification Service.
the spindle bolt for a crack in areas Z1 and proposal to: Martin R. Crane, Aviation Safety [FR Doc. 2018–04647 Filed 3–8–18; 8:45 am]
Z2 as depicted in Figure 2 of EASB 64.00.43. Engineer, Regulations & Policy Section,
BILLING CODE 4910–13–P
If there is a crack, before further flight, record Rotorcraft Standards Branch, FAA, 10101
that there is a crack and remove from service Hillwood Pkwy., Fort Worth, TX 76177;
the spindle bolt, hexagonal castellated nut, telephone (817) 222–5110; email 9-ASW-
inner ring, stop washers, needle bearings or FTW-AMOC-Requests@faa.gov. DEPARTMENT OF TRANSPORTATION
set of needle bearings, seals, and split (2) For operations conducted under a 14
washer. CFR part 119 operating certificate or under Federal Aviation Administration
(iv) Remove the inner ring and stop 14 CFR part 91, subpart K, we suggest that
washers. you notify your principal inspector, or 14 CFR Part 97
(v) Inspect the bearing race inner ring and lacking a principal inspector, the manager of
the local flight standards district office or [Docket No. 31181; Amdt. No. 3789]
bearing needles for spalling. If there is any
spalling, before further flight, record that certificate holding district office, before
operating any aircraft complying with this Standard Instrument Approach
there is spalling and replace the bearing race.
(vi) Measure the thickness of each stop
AD through an AMOC. Procedures, and Takeoff Minimums
washer. If the thickness is less than 1.5 mm (h) Additional Information and Obstacle Departure Procedures;
(.060 inch), before further flight, remove the Miscellaneous Amendments
The subject of this AD is addressed in
stop washer from service. Record that the European Aviation Safety Agency (EASA) AGENCY: Federal Aviation
stop washer was removed from service Emergency AD No. 2017–0232–E, dated Administration (FAA), DOT.
because of thickness. November 21, 2017. You may view the EASA
(vii) Inspect the inner ring for brinelling. AD on the internet at http:// ACTION: Final rule.
(A) If there is brinelling more than 0.1 mm www.regulations.gov by searching for and
(.004 inch) in depth, before further flight, locating it in Docket No. FAA–2018–0177. SUMMARY: This rule establishes, amends,
record that there is brinelling and repair the suspends, or removes Standard
(i) Subject Instrument Approach Procedures
hinge.
(B) If there is brinelling 0.1 mm (.004 inch) Joint Aircraft Service Component (JASC) (SIAPs) and associated Takeoff
or less in depth, before further flight, turn the Code: 6420 Tail Rotor Head. Minimums and Obstacle Departure
inner ring to position the area with brinelling (j) Material Incorporated by Reference Procedures (ODPs) for operations at
on the T/R hub pin side. Record the certain airports. These regulatory
brinelling and the turning of the inner ring. (1) The Director of the Federal Register
approved the incorporation by reference of actions are needed because of the
Dye-penetrant inspect the inner ring for a adoption of new or revised criteria, or
the service information listed in this
crack in the area depicted as ‘‘Z3’’ of Figure because of changes occurring in the
paragraph under 5 U.S.C. 552(a) and 1 CFR
3 of EASB 64.00.43. If there is a crack, before
part 51. National Airspace System, such as the
further flight, record that there is a crack in (2) You must use this service information
the inner ring and remove from service the commissioning of new navigational
as applicable to do the actions required by facilities, adding new obstacles, or
spindle bolt, hexagonal castellated nut, inner this AD, unless the AD specifies otherwise.
ring, stop washers, needle bearings or set of changing air traffic requirements. These
(i) Airbus Helicopters Emergency Alert
needle bearings, seals, and split washer. Service Bulletin (EASB) No. 64.00.43, changes are designed to provide safe
(2) Within 10 days after the inspection, Revision 0, dated November 21, 2017. and efficient use of the navigable
submit a report of the measurements and (ii) Reserved. airspace and to promote safe flight
findings of the inspection required by Note 1 to paragraph (j)(2): Airbus operations under instrument flight rules
paragraph (e)(1) of this AD, as specified in Helicopters EASB No. 64.00.43, Revision 0, at the affected airports.
the Appendix of EASB 64.00.43, to dated November 21, 2017, is co-published as DATES: This rule is effective March 9,
support.technical-dyncomp.ah@airbus.com. one document along with Airbus Helicopters 2018. The compliance date for each
(f) Paperwork Reduction Act Burden EASB No. 64.00.21, Revision 0, dated SIAP, associated Takeoff Minimums,
Statement November 21, 2017, which is not
incorporated by reference.
and ODP is specified in the amendatory
A federal agency may not conduct or provisions.
(3) For Airbus Helicopters service
sponsor, and a person is not required to The incorporation by reference of
information identified in this AD, contact
respond to, nor shall a person be subject to certain publications listed in the
Airbus Helicopters, 2701 N. Forum Drive,
a penalty for failure to comply with a regulations is approved by the Director
Grand Prairie, TX 75052; telephone (972)
collection of information subject to the 641–0000 or (800) 232–0323; fax (972) 641– of the Federal Register as of March 9,
requirements of the Paperwork Reduction 3775; or at http:// 2018.
Act unless that collection of information www.helicopters.airbus.com/website/en/ref/
displays a current valid OMB Control Technical-Support_73.html. ADDRESSES: Availability of matters
Number. The OMB Control Number for this (4) You may view this service information incorporated by reference in the
information collection is 2120–0056. Public at FAA, Office of the Regional Counsel, amendment is as follows:
reporting for this collection of information is Southwest Region, 10101 Hillwood Pkwy,
estimated to be approximately 30 minutes Room 6N–321, Fort Worth, TX 76177. For For Examination
per response, including the time for information on the availability of this 1. U.S. Department of Transportation,
reviewing instructions, completing and material at the FAA, call (817) 222–5110. Docket Ops-M30, 1200 New Jersey
reviewing the collection of information. All (5) You may view this service information Avenue SE, West Bldg., Ground Floor,
amozie on DSK30RV082PROD with RULES
responses to this collection of information that is incorporated by reference at the
are mandatory. Comments concerning the
Washington, DC, 20590–0001.
National Archives and Records
accuracy of this burden and suggestions for Administration (NARA). For information on 2. The FAA Air Traffic Organization
reducing the burden should be directed to the availability of this material at NARA, call Service Area in which the affected
the FAA at: 800 Independence Ave. SW, (202) 741–6030, or go to: http:// airport is located;
Washington, DC 20591, Attn: Information www.archives.gov/federal-register/cfr/ibr- 3. The office of Aeronautical
Collection Clearance Officer, AES–200. locations.html. Navigation Products, 6500 South
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Document Created: 2018-03-09 03:48:56
Document Modified: 2018-03-09 03:48:56
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective March 26, 2018. | |
| Contact | Martin R. Crane, Aviation Safety Engineer, Regulations & Policy Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222- 5110; email [email protected] | |
| FR Citation | 83 FR 10360 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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