80 FR 53024 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France (Eurocopter) Helicopters)
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 170 (September 2, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 170 (September 2, 2015)
| Page Range | 53024-53028 | |
| FR Document | 2015-21689 |
[Federal Register Volume 80, Number 170 (Wednesday, September 2, 2015)] [Proposed Rules] [Pages 53024-53028] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-21689] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3657; Directorate Identifier 2012-SW-069-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France (Eurocopter) Helicopters) AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- [[Page 53025]] SUMMARY: We propose to supersede airworthiness directive (AD) 2007-25- 08 for Eurocopter Model SA-365 N1, AS-365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2007-25-08 currently requires checking the tail rotor gearbox (TGB) oil level, inspecting the magnetic plug for chips and either replacing the TGB or further inspecting for axial play in the tail rotor hub pitch change control spider (spider), and if axial play is found in the spider, replacing the pitch control rod assembly double bearing (bearing). Since we issued the AD 2007-25-08, we have received reports of new occurrences of loss of yaw control due to failure of the control rod bearing. This proposed AD would retain some of the requirements of AD 2007-25-08, revise the inspections for play in the double bearing to improve the detection of play, require replacing the TGB control shaft guide bushes, clarify the criteria concerning particle detection, and change the inspection for play in the double bearing after the guide bushes have been replaced. The proposed actions are intended to prevent damage to the bearing resulting in end play, loss of tail rotor pitch control, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by November 2, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. Fax: 202-493-2251. Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001. Hand Delivery: Deliver to the ``Mail'' address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received and other information. The street address for the Docket Operations Office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub. You may review service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, Texas 76177. FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, Texas 76177; telephone (817) 222-5110; email [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion On November 27, 2007, we issued AD 2007-25-08, Amendment 39-15290 (72 FR 69604, December 10, 2007) for Eurocopter (now Airbus Helicopters) Model SA-365 N1, AS-365 N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2007-25-08 requires repetitively checking the TGB oil level to ensure it is at the maximum level. AD 2007-25-08 also requires repetitively inspecting the magnetic plug for chips, and depending on the quantity of chips found, either replacing the TGB or further inspecting for axial play in the spider. If axial play is found in the spider, AD 2007-25-08 requires replacing the bearing. AD 2007- 25-08 was prompted by EASA Emergency AD No. 2006-0258R1-E, dated August 29, 2006, as well as the finding that metal chips were not detected on the magnetic plug due to insufficient oil flow because the oil in the TGB was being maintained at the minimum level. The actions of AD 2007- 25-08 are intended to detect metal chips on the magnetic plug and to prevent damage to the bearing resulting in end play, loss of tail rotor pitch control, and subsequent loss of control of the helicopter. Actions Since AD 2007-25-08 Was Issued Since we issued AD 2007-25-08 (72 FR 69604, December 10, 2007), we have received reports of new occurrences of loss of yaw control due to failure of the control rod bearing. EASA, which is the Technical Agent for the Member States of the European Union, has since superseded EASA Emergency AD No. 2006-0258R1- E with several ADs, the most recent being EASA AD No. 2012-0170R2, dated June 20, 2014, to correct an unsafe condition for these Airbus Model helicopters. After receiving reports of several new occurrences of damage to the bearings and subsequent investigations of the incidents, EASA advises of implementing additional, revised inspection and corrective actions; reducing the interval between inspections; a modification replacing both guide bushes and improving the tolerance between the control shaft and the TGB wheel to limit the friction loads on the control bearing; and requiring the play measurement of the TGB to control rod, shaft assembly double bearing to be measured according to the type of fenestron installed. EASA AD 2012-0170R2 also excludes helicopters modified in accordance with modification (MOD) 07 65B63. 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 its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design. [[Page 53026]] Related Service Information Under 1 CFR Part 51 We reviewed ASB No. AS365-05.00.61, Revision 4, dated April 8, 2014, for FAA-certificated Model SA 365 N1, AS 365 N2, and AS 365 N3 helicopters and for non-FAA-certificated Model AS355F, F1, and F2 helicopters; ASB No. SA366-05.41, Revision 4, dated April 8, 2014, for FAA-certificated Model SA-366G1 and non-FAA-certificated Model SA-366GA helicopters; and ASB No. EC155-05A022, Revision 4, dated April 8, 2014, for FAA-certificated Model EC 155B and EC155B1 helicopters. All three ASBs describe procedures for monitoring the behavior of the bearing by checking its axial play by dimensional measurement and by maintaining the operating oil at the maximum level. EASA classified this service information as mandatory and issued EASA AD No. 2012-0170R2 to ensure the continued airworthiness of these helicopters. 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 of this NPRM. Proposed AD Requirements This proposed AD would require: Checking the TGB oil level at specified intervals. An owner/operator (pilot) may perform this visual check and must enter compliance into the helicopter maintenance records in accordance with 14 CFR Sec. Sec. 43.9(a)(1) through (4) and 91.417(a)(2)(v). A pilot may perform this check because it involves only a visual check for the oil level in the TGB and can be performed equally well by a pilot or a mechanic. This check is an exception to our standard maintenance regulations. Inspecting the magnetic plug of the TGB for chips at specified intervals. Within 300 hours time-in-service (TIS), replacing each affected part-numbered TGB guide bush with an airworthy guide bush, inspecting the bearing of the TGB control shaft and rod assembly for M50 type particles, and performing measurements of play in the TGB control shaft and rod assembly. Within 110 hours TIS after replacing the guide bush, and thereafter at intervals not to exceed 55 hours TIS, performing certain measurements for play in the TGB control shaft and rod assembly. This proposed AD would not apply to helicopters with TGB part number 365A33-6005-09 installed. Airbus Helicopters refers to the installation of this part-numbered TGB as MOD 07 65B63. Differences Between the Proposed AD and the EASA AD The calendar times in the EASA AD have already passed and are not included in this proposed AD. Costs of Compliance We estimate that this proposed AD would affect 133 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. The estimated labor cost is $85 per work-hour. We estimate .5 work-hour to check the TGB oil level for a cost of $43 per helicopter and $5,719 for the fleet each inspection cycle. We estimate .5 work-hour to inspect the magnetic plug on the TGB for chips for a cost of $43 per helicopter and $5,719 for the fleet each inspection cycle. We estimate 3 work-hours to measure the play in the TGB control shaft and rod assembly for a cost of $255 per helicopter and $33,915 for the fleet each inspection cycle. Replacing the TGB control shaft guide bushes would take 4 work-hours and required parts would cost $565, for an estimated total of $905 per helicopter and $120,365 for the U.S. operator fleet. Inspecting the TGB control shaft and rod assembly for steel particles would take 6 work-hours for a cost per helicopter of $510 and a fleet cost of $67,830. If necessary, it would cost about $30,000 per helicopter to replace the TGB and $24,000 for overhaul of the TGB to replace the bearing. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2007-25-08, Amendment 39-15290 (72 FR 69604, December 10, 2007), and adding the following new AD: Airbus Helicopters (Previously Eurocopter France Helicopters): Docket No. FAA-2015-3657; Directorate Identifier 2012-SW-069-AD. (a) Applicability This AD applies to Model SA-365N1, AS-365N2, AS 365 N3, SA- 366G1, EC 155B, and EC155B1 helicopters, with a tail rotor gearbox (TGB) pitch control rod assembly double bearing (bearing) installed, certificated in any category, except helicopters with TGB part number (P/N) 365A33-6005-09 installed. (b) Unsafe Condition This AD defines the unsafe condition as damage to the bearing, which could result in end play, loss of tail rotor pitch control, and subsequent loss of control of the helicopter. [[Page 53027]] (c) Affected ADs This AD supersedes AD 2007-25-08, Amendment 39-15290 (72 FR 69604, December 10, 2007). (d) Comments Due Date We must receive comments by November 2, 2015. (e) 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. (f) Required Actions (1) Check the TGB oil level at the following intervals: (i) For Model SA-365N1, AS-365N2, AS 365 N3 helicopters, at intervals not to exceed 10 hours time-in-service (TIS). (ii) For Model SA366G1 helicopters, at each daily flight check. (iii) For Model EC 155B and EC155B1 helicopters, at intervals not to exceed 15 hours TIS or 7 days, whichever occurs first. (iv) The actions required by paragraph (f)(1) of this AD may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR Sec. Sec. 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR Sec. Sec. 91.417, 121.380, or 135.439. (2) If the oil level is not at maximum, before further flight, a qualified mechanic must fill it to the maximum level. (3) Inspect the magnetic plug of the TGB for any chips as follows: (i) At intervals not to exceed 25 hours TIS for helicopters with a magnetic plug without a chip electrical indication in the cockpit, or (ii) At intervals not to exceed 100 hours TIS and after any illumination of the TGB ``CHIP'' warning light for helicopters with a chip electrical indication in the cockpit. (4) If you find any chips during the inspection in paragraph (f)(3) of this AD, determine whether the quantity of chips is within the removal criteria. (i) If the quantity of chips on the magnetic plug is at or above the removal criteria, before further flight, replace the TGB with an airworthy TGB. (ii) If the quantity of chips on the magnetic plug is below the removal criteria, comply with paragraph (f)(6) of this AD before further flight. (5) Within 300 hours TIS, without removing the TGB: (i) Replace each TGB control shaft guide bush (guide bush), P/N 365A33-6189-20 and 365A33-6189-21, with guide bush, P/N 365A33-6223- 20, and replace each guide bush, P/N 365A33-6188-20, with guide bush, P/N 365A33-6222-20. Note 1 to paragraph (f)(5)(i) of this AD: Airbus Helicopters refers to the replacement of the guide bushes as Modification 0765B58. (ii) Inspect the bearing of the TGB control shaft and rod assembly for M50 type particles (particles) as shown in Figures 1 through 3 of Airbus Helicopters Alert Service Bulletin (ASB) No. AS365-05.00.61, Revision 4, dated April 8, 2014, for Model SA 365 N1, AS 365 N2, and AS 365 N3 helicopters (AS365-05.00.61); ASB No. SA366-05.41, Revision 4, dated April 8, 2014, for Model SA 366G1 helicopters (SA366-05.41); or ASB No. EC155-05A022, Revision 4, dated April 8, 2014, for Model EC 155B and EC155B1 helicopters (EC155-05A022). Inspect the bearing by separating the control shaft (item q of Figure 3) from the control rod (item p of Figure 3), rinse the bearing with white spirit or equivalent, collect the product on a blotting paper, and inspect for particles inside the control shaft, around the bearing, and on blotting paper. (A) If there are no particles, clean the control shaft and control rod with white spirit or equivalent and install the control shaft and control rod. (B) If there are any particles, replace the bearing with an airworthy bearing. (iii) Perform measurements of play in the TGB control shaft and rod assembly bearing as follows: (A) For the TGB side: (1) Remove the cover and inspect the positioning of the locking of the 3 screws, as shown in the two positioning for measurement photographs in the Accomplishment Instructions under paragraph 3.B.4.a.(1) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022. Correctly lock the screws if the positioning is inconvenient for measurement. Set the pedal unit to the neutral position and rig the tail servo-control using a 6 mm diameter pin. Remove any primer and paint from the support casing face of the servo-control using 600 grit sand paper. Apply DOW 19 or equivalent protection and a coat of primer P05 or equivalent. Do not reapply primer and paint to the support casing face of the servo-control. (2) Perform a measurement ``M1'' using a caliper gage, between the end of the control rod (item p in the three photographs in the Accomplishment Instructions under paragraph 3.B.4.a.(1) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) and the seating face of the servo-control on the casing. Mark the position of the caliper gage on the support casing face of the servo-control as ``R1'' using a permanent felt tip pen. Position the caliper gage on R1 (shown in the first of the three photographs in the Accomplishment Instructions under paragraph 3.B.4.a.(1) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) and on the screw (item ac in the first of the three photographs in the Accomplishment Instructions under paragraph 3.B.4.a.(1) of ASB AS365-05.00.61, SA336-05.41, or EC155- 05A022) of the universal joint of the servo-control. Set the mobile part of the caliper gage against the end of the control rod. Shift the caliper gage against the control lever (item ab in the last photograph in the Accomplishment Instructions under paragraph 3.B.4.a.(1) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) while remaining in contact with the end of the control rod. (3) Record measurement M1 indicated on the caliper gage on the component history card or equivalent record. (B) For the TRH side: (1) Perform a measurement ``M2'' using a caliper gage between the flat face of the center plate (item c in the photograph in the Accomplishment Instructions under paragraph 3.B.4.a.(2) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) and the face of the inner web (item ad in the photograph in the Accomplishment Instructions under paragraph 3.B.4.a.(2) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) of the rotor hub on which the inner bearings of the TRH blades are installed. Position the caliper gage flat across the opening (item ae in the photograph in the Accomplishment Instructions under paragraph 3.B.4.a.(2) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) of the pitch change spider. Mark the position of the caliper gage on the flat surface of the center plate as ``R2'' and on the opening as ``R3'' using a permanent felt tip pen. (2) Record measurement M2 indicated on the caliper gage. (3) Calculate a measurement ``M0'' by adding measurements M1 (required in paragraph (f)(5)(iii)(A) of this AD) and M2. (4) Perform measurements M1 and M2 again by repeating the requirements in paragraphs (f)(5)(iii)(A) and (f)(5)(iii)(B) of this AD and calculate a second measurement M0. (5) Calculate the difference between the two M0 measurements. If the difference is not less than 0.25 mm (0.01 inch), calculate the two M0 measurements again. (6) Calculate the mean value of the two M0 measurements and record it on the component history card or equivalent record. This M0 measurement will be the reference measurement enabling you to evaluate any increase in the play in the bearing of the control shaft and rod assembly during later inspections. (6) Within 110 hours TIS after replacing the guide bush, and thereafter at intervals not to exceed 55 hours TIS, perform measurements for play in the TGB control shaft and rod assembly as follows. (i) On the TGB side: (A) Remove the TGB fairing, set the pedal unit to the neutral position and rig the tail servo-control using a 6 mm diameter pin. (B) Perform measurement ``M1'' using a caliper gage between the end of the control rod (item p in the three photographs in the Accomplishment Instructions under paragraph 3.B.4.b (1) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) and the seating face of the servo-control on the casing. Position the caliper gage on mark R1 and the bearing against the screw (item ac as shown in the first of the three photographs in the Accomplishment Instructions under paragraph 3.B.4.b.(1) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) of the universal joint of the servo-control. Set the mobile part of the caliper gage against the end of the control rod. Shift the caliper gage against the control lever (item ab as shown in the last of the three photographs in the Accomplishment Instructions under paragraph 3.B.4.b.(1) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) while remaining in contact with the end of the control rod. [[Page 53028]] (C) Record measurement M1 indicated on the caliper gage on the component history card or equivalent record. (ii) On the tail rotor hub (TRH) side: (A) Remove the fairing and perform a measurement ``M2'' using a caliper gage between the flat face of the center plate (item c in the photograph in the Accomplishment Instructions under paragraph 3.B.4.b.(2) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) and the face of the inner web (item ad in the photograph in the Accomplishment Instructions under paragraph 3.B.4.b.(2) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022) of the rotor hub on which the inner bearings of the TRH blades are installed. Position the caliper gage flat across the opening of the pitch change spider on R2 and R3 as shown in the right photograph in the Accomplishment Instructions under paragraph 3.B.4.b.(2) of ASB AS365-05.00.61, SA336-05.41, or EC155-05A022. (B) Record measurement M2 indicated on the caliper gage on the component history card or equivalent record. (C) Calculate a measurement ``M3'' by adding measurements M1 and M2. (D) Calculate the difference between measurement ``M0'' indicated on the TGB component history card or equivalent record and M3. (1) If the difference between measurement M0 and M3 is less than 0.5 mm (0.02 inch), perform an additional inspection for play in the bearing of the TGB control shaft and rod assembly by following the Accomplishment Instructions, paragraph 3.B.6., of ASB AS365- 05.00.61, SA366-05.41, or EC155-05A022. If there is no axial play at the TRH pitch change spider, record value M3 on the component history card or equivalent record. If there is axial play at the TRH pitch change spider, replace the bearing with an airworthy bearing and perform a new reference measurement by following the requirements of paragraph (f)(6) of this AD. (2) If the difference between the measurements is equal to or greater than 0.5 mm (0.02 inch), replace the bearing with an airworthy bearing and perform a new reference measurement by following the requirements of paragraph (f)(6) of this AD. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, Texas 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) AD No. 2012-0170R2, dated June 20, 2014. You may view the EASA AD on the internet at http://www.regulations.gov in Docket No. FAA-2015-3657. (i) Subject Joint Aircraft Service Component (JASC) Code: 6520 Tail Rotor Gearbox. Issued in Fort Worth, Texas, on August 21, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-21689 Filed 9-1-15; 8:45 am] BILLING CODE 4910-13-P
![53024 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules
be generated at the higher assessment Regarding the impact of this action on the FOR FURTHER INFORMATION CONTACT
rate for the committee to meet its affected entities, this action would section.
anticipated expenses. increase the assessment obligation A 30-day comment period is provided
The major expenditures imposed on handlers. While increased to allow interested persons to respond
recommended by the committee for the assessments impose additional costs on to this proposed rule. Thirty days is
2015–16 crop year include: Salaries and handlers regulated under the order, the deemed appropriate because: (1) The
employee-related costs of $1,402,906; rates are uniform on all handlers, and 2015–16 crop year begins on August 1,
administration costs of $610,000; proportional to the size of their 2015, and the order requires the rate of
compliance activities of $30,000; businesses. It is expected that these assessment for each crop year to apply
research of $129,000; operation and costs would be offset by the benefits to all assessable raisins handled during
maintenance of generic marketing derived from the operation of the order. the crop year; (2) the committee needs
programs of $3,520,178; and a In addition, the meetings of the Audit to have sufficient funds to pay its
contingency of $355,503. and Marketing Subcommittees, and the expenses, which are incurred on a
In comparison, last year’s approved full committee were widely publicized continuous basis; and (3) handlers are
budgeted expenditures included: throughout the California raisin aware of this action, which was
Salaries and employee-related costs of industry, and all interested persons unanimously recommended by the
$1,337,100; administration costs of were invited to attend the meetings and committee at a public meeting.
$493,500; compliance activities of encouraged to participate in committee
deliberations on all issues. Like all List of subjects in 7 CFR Part 989
$30,000; research of $85,000; operation
and maintenance of generic marketing subcommittee and committee meetings, Grapes, Marketing agreements,
programs of $3,296,800; and a the June 8, 2015 and June 11, 2015, Raisins, Reporting and recordkeeping
contingency of $100,000. The total meetings were public meetings, and all requirements.
budget approved for the 2014–15 crop entities, both large and small, were able For the reasons set forth in the
year was $5,175,540. to express views on this issue. Finally, preamble, 7 CFR part 989 is proposed to
The committee believes that more interested persons are invited to submit be amended as follows:
funds should be spent in promoting comments on this proposed rule,
including the regulatory and PART 989—RAISINS PRODUCED
raisins internationally, including China.
informational impacts of this action on FROM GRAPES GROWN IN
For that reason, expenses for research
small businesses. CALIFORNIA
and promotion activities have been
In accordance with the Paperwork
increased: Operation and maintenance ■ 1. The authority citation for 7 CFR
Reduction Act of 1995 (44 U.S.C.
of generic marketing programs increased part 989 continues to read as follows:
Chapter 35), the order’s information
from $3,296,800 for the 2014–15 crop collection requirements have been Authority: 7 U.S.C. 601–674.
year to $3,520,178 for the 2015–16 crop previously approved by the Office of
year, and research has increased from ■ 2. Section 989.347 is revised to read
Management and Budget (OMB) and
$85,000 for the 2014–15 crop year to as follows:
assigned OMB No. 0581–0178,
$129,000 for the 2015–16 crop year. In ‘‘Vegetable and Specialty Crops.’’ No § 989.347 Assessment rate.
order to fund these additional proposed changes in those requirements as a
expenditures, the committee On and after August 1, 2015, an
result of this action are necessary. assessment rate of $17.00 per ton is
recommended an increased assessment Should any changes become necessary,
rate. established for assessable raisins
they would be submitted to OMB for produced from grapes grown in
Pursuant to § 989.81(a) of the order, approval.
any unexpended assessment funds from California.
This proposed rule would impose no
the crop year must be credited or additional reporting or recordkeeping Dated: August 28, 2015.
refunded to the handlers from whom requirements on either small or large Rex A. Barnes,
collected. California raisin handlers. As with all Associate Administrator, Agricultural
Prior to arriving at this budget and Federal marketing order programs, Marketing Service.
assessment rate, the committee reports and forms are periodically [FR Doc. 2015–21850 Filed 9–1–15; 8:45 am]
considered information from various reviewed to reduce information BILLING CODE P
sources, such as the committee’s Audit requirements and duplication by
and Marketing Subcommittees. industry and public sector agencies.
Alternative spending levels were AMS is committed to complying with DEPARTMENT OF TRANSPORTATION
discussed by the Marketing and Audit the E-Government Act, to promote the
Subcommittees, which met on June 8, use of the internet and other Federal Aviation Administration
2015 and June 11, 2015, to review the information technologies to provide
committee’s financial operations. increased opportunities for citizen 14 CFR Part 39
The committee ultimately decided access to Government information and [Docket No. FAA–2015–3657; Directorate
that the recommended budget and services, and for other purposes. Identifier 2012–SW–069–AD]
assessment rate were reasonable and USDA has not identified any relevant
necessary to properly administer the Federal rules that duplicate, overlap, or RIN 2120–AA64
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
order. conflict with this action.
A review of statistical data on the A small business guide on complying Airworthiness Directives; Airbus
California raisin industry indicates that with fruit, vegetable, and specialty crop Helicopters (Previously Eurocopter
assessment revenue has consistently marketing agreements and orders may France (Eurocopter) Helicopters)
been less than one percent of grower be viewed at: http://www.ams.usda.gov/ AGENCY: Federal Aviation
revenue in recent years. With a $17.00 MarketingOrdersSmallBusinessGuide. Administration (FAA), DOT.
assessment rate, assessment revenue Any questions about the compliance
ACTION: Notice of proposed rulemaking
would be expected to remain at less guide should be sent to Jeffrey Smutny
(NPRM).
than one percent of grower revenue. at the previously mentioned address in
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![53026 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules
Related Service Information Under 1 Differences Between the Proposed AD substantial direct effect on the States, on
CFR Part 51 and the EASA AD the relationship between the national
We reviewed ASB No. AS365– The calendar times in the EASA AD Government and the States, or on the
05.00.61, Revision 4, dated April 8, have already passed and are not distribution of power and
2014, for FAA-certificated Model SA included in this proposed AD. responsibilities among the various
365 N1, AS 365 N2, and AS 365 N3 levels of government.
Costs of Compliance For the reasons discussed, I certify
helicopters and for non-FAA-
certificated Model AS355F, F1, and F2 We estimate that this proposed AD this proposed regulation:
helicopters; ASB No. SA366–05.41, would affect 133 helicopters of U.S. 1. Is not a ‘‘significant regulatory
Revision 4, dated April 8, 2014, for Registry. We estimate that operators action’’ under Executive Order 12866;
FAA-certificated Model SA–366G1 and may incur the following costs in order 2. Is not a ‘‘significant rule’’ under the
non-FAA-certificated Model SA–366GA to comply with this AD. The estimated DOT Regulatory Policies and Procedures
helicopters; and ASB No. EC155– labor cost is $85 per work-hour. We (44 FR 11034, February 26, 1979);
05A022, Revision 4, dated April 8, 2014, estimate .5 work-hour to check the TGB 3. Will not affect intrastate aviation in
for FAA-certificated Model EC 155B and oil level for a cost of $43 per helicopter Alaska to the extent that it justifies
EC155B1 helicopters. All three ASBs and $5,719 for the fleet each inspection making a regulatory distinction; and
describe procedures for monitoring the cycle. We estimate .5 work-hour to 4. Will not have a significant
behavior of the bearing by checking its inspect the magnetic plug on the TGB economic impact, positive or negative,
axial play by dimensional measurement for chips for a cost of $43 per helicopter on a substantial number of small entities
and by maintaining the operating oil at and $5,719 for the fleet each inspection under the criteria of the Regulatory
the maximum level. EASA classified cycle. We estimate 3 work-hours to Flexibility Act.
this service information as mandatory measure the play in the TGB control We prepared an economic evaluation
and issued EASA AD No. 2012–0170R2 shaft and rod assembly for a cost of $255 of the estimated costs to comply with
per helicopter and $33,915 for the fleet this proposed AD and placed it in the
to ensure the continued airworthiness of
each inspection cycle. Replacing the AD docket.
these helicopters. This service
TGB control shaft guide bushes would
information is reasonably available List of Subjects in 14 CFR Part 39
take 4 work-hours and required parts
because the interested parties have
would cost $565, for an estimated total Air transportation, Aircraft, Aviation
access to it through their normal course
of $905 per helicopter and $120,365 for safety, Incorporation by reference,
of business or by the means identified
the U.S. operator fleet. Inspecting the Safety.
in the ADDRESSES section of this NPRM.
TGB control shaft and rod assembly for
Proposed AD Requirements steel particles would take 6 work-hours The Proposed Amendment
This proposed AD would require: for a cost per helicopter of $510 and a Accordingly, under the authority
• Checking the TGB oil level at fleet cost of $67,830. If necessary, it delegated to me by the Administrator,
specified intervals. An owner/operator would cost about $30,000 per helicopter the FAA proposes to amend 14 CFR part
(pilot) may perform this visual check to replace the TGB and $24,000 for 39 as follows:
and must enter compliance into the overhaul of the TGB to replace the
bearing. PART 39—AIRWORTHINESS
helicopter maintenance records in
accordance with 14 CFR §§ 43.9(a)(1) Authority for This Rulemaking DIRECTIVES
through (4) and 91.417(a)(2)(v). A pilot Title 49 of the United States Code
may perform this check because it ■ 1. The authority citation for part 39
specifies the FAA’s authority to issue continues to read as follows:
involves only a visual check for the oil rules on aviation safety. Subtitle I,
level in the TGB and can be performed Authority: 49 U.S.C. 106(g), 40113, 44701.
section 106, describes the authority of
equally well by a pilot or a mechanic. the FAA Administrator. ‘‘Subtitle VII: § 39.13 [Amended]
This check is an exception to our Aviation Programs,’’ describes in more
standard maintenance regulations. ■ 2. The FAA amends § 39.13 by
detail the scope of the Agency’s
• Inspecting the magnetic plug of the authority.
removing Airworthiness Directive (AD)
TGB for chips at specified intervals. We are issuing this rulemaking under 2007–25–08, Amendment 39–15290 (72
• Within 300 hours time-in-service the authority described in ‘‘Subtitle VII, FR 69604, December 10, 2007), and
(TIS), replacing each affected part- Part A, Subpart III, Section 44701: adding the following new AD:
numbered TGB guide bush with an General requirements.’’ Under that Airbus Helicopters (Previously Eurocopter
airworthy guide bush, inspecting the section, Congress charges the FAA with France Helicopters): Docket No. FAA–
bearing of the TGB control shaft and rod promoting safe flight of civil aircraft in 2015–3657; Directorate Identifier 2012–
assembly for M50 type particles, and air commerce by prescribing regulations SW–069–AD.
performing measurements of play in the for practices, methods, and procedures (a) Applicability
TGB control shaft and rod assembly. the Administrator finds necessary for This AD applies to Model SA–365N1, AS–
• Within 110 hours TIS after safety in air commerce. This regulation 365N2, AS 365 N3, SA–366G1, EC 155B, and
replacing the guide bush, and thereafter is within the scope of that authority EC155B1 helicopters, with a tail rotor
at intervals not to exceed 55 hours TIS, because it addresses an unsafe condition gearbox (TGB) pitch control rod assembly
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
performing certain measurements for that is likely to exist or develop on double bearing (bearing) installed,
play in the TGB control shaft and rod products identified in this rulemaking certificated in any category, except
assembly. action. helicopters with TGB part number (P/N)
This proposed AD would not apply to 365A33–6005–09 installed.
helicopters with TGB part number Regulatory Findings (b) Unsafe Condition
365A33–6005–09 installed. Airbus We determined that this proposed AD This AD defines the unsafe condition as
Helicopters refers to the installation of would not have federalism implications damage to the bearing, which could result in
this part-numbered TGB as MOD 07 under Executive Order 13132. This end play, loss of tail rotor pitch control, and
65B63. proposed AD would not have a subsequent loss of control of the helicopter.
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![53028 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules
(C) Record measurement M1 indicated on No. 2012–0170R2, dated June 20, 2014. You • Fax: 202–493–2251.
the caliper gage on the component history may view the EASA AD on the internet at • Mail: Send comments to the U.S.
card or equivalent record. http://www.regulations.gov in Docket No. Department of Transportation, Docket
(ii) On the tail rotor hub (TRH) side: FAA–2015–3657.
(A) Remove the fairing and perform a
Operations, M–30, West Building
measurement ‘‘M2’’ using a caliper gage (i) Subject Ground Floor, Room W12–140, 1200
between the flat face of the center plate (item Joint Aircraft Service Component (JASC) New Jersey Avenue SE., Washington,
c in the photograph in the Accomplishment Code: 6520 Tail Rotor Gearbox. DC 20590–0001.
Instructions under paragraph 3.B.4.b.(2) of Issued in Fort Worth, Texas, on August 21, • Hand Delivery: Deliver to the
ASB AS365–05.00.61, SA336–05.41, or 2015. ‘‘Mail’’ address between 9 a.m. and 5
EC155–05A022) and the face of the inner web p.m., Monday through Friday, except
(item ad in the photograph in the Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Federal holidays.
Accomplishment Instructions under
paragraph 3.B.4.b.(2) of ASB AS365– Directorate, Aircraft Certification Service. Examining the AD Docket
05.00.61, SA336–05.41, or EC155–05A022) of [FR Doc. 2015–21689 Filed 9–1–15; 8:45 am]
the rotor hub on which the inner bearings of You may examine the AD docket on
BILLING CODE 4910–13–P
the TRH blades are installed. Position the the Internet at http://
caliper gage flat across the opening of the www.regulations.gov or in person at the
pitch change spider on R2 and R3 as shown Docket Operations Office between 9
in the right photograph in the DEPARTMENT OF TRANSPORTATION
a.m. and 5 p.m., Monday through
Accomplishment Instructions under Friday, except Federal holidays. The AD
paragraph 3.B.4.b.(2) of ASB AS365– Federal Aviation Administration
05.00.61, SA336–05.41, or EC155–05A022.
docket contains this proposed AD, the
(B) Record measurement M2 indicated on 14 CFR Part 39 economic evaluation, any comments
the caliper gage on the component history received, and other information. The
card or equivalent record. [Docket No. FAA–2015–3659; Directorate street address for the Docket Operations
(C) Calculate a measurement ‘‘M3’’ by Identifier 2014–SW–050–AD] Office (telephone 800–647–5527) is in
adding measurements M1 and M2. RIN 2120–AA64 the ADDRESSES section. Comments will
(D) Calculate the difference between be available in the AD docket shortly
measurement ‘‘M0’’ indicated on the TGB Airworthiness Directives; MD after receipt.
component history card or equivalent record Helicopters Inc., Helicopters
and M3.
For service information identified in
(1) If the difference between measurement AGENCY: Federal Aviation this proposed AD, contact Aerometals,
M0 and M3 is less than 0.5 mm (0.02 inch), Administration (FAA), DOT. 3920 Sandstone Dr., El Dorado Hills, CA
perform an additional inspection for play in 95762, telephone (916) 939–6888, fax
ACTION: Notice of proposed rulemaking
the bearing of the TGB control shaft and rod (916) 939–6555, www.aerometals.aero.
assembly by following the Accomplishment (NPRM).
You may review the referenced service
Instructions, paragraph 3.B.6., of ASB SUMMARY: We propose to adopt a new information at the FAA, Office of the
AS365–05.00.61, SA366–05.41, or EC155– Regional Counsel, Southwest Region,
05A022. If there is no axial play at the TRH airworthiness directive (AD) for MD
pitch change spider, record value M3 on the Helicopters Inc. (MDHI) Model 369A, 10101 Hillwood Pkwy, Room 6N–321,
component history card or equivalent record. 369D, 369E, 369FF, 369HE, 369HM, Fort Worth, TX 76177.
If there is axial play at the TRH pitch change 369HS, 500N, and 600N helicopters FOR FURTHER INFORMATION CONTACT:
spider, replace the bearing with an airworthy with a certain part-numbered main rotor Galib Abumeri, Aviation Safety
bearing and perform a new reference blade attach pin (pin) installed. This Engineer, Los Angeles Aircraft
measurement by following the requirements proposed AD would require ensuring Certification Office, Transport Airplane
of paragraph (f)(6) of this AD. the life limit of the pin as listed in the
(2) If the difference between the
Directorate, FAA, 3960 Paramount
measurements is equal to or greater than 0.5 Airworthiness Limitations section of Blvd., Lakewood, California 90712;
mm (0.02 inch), replace the bearing with an aircraft maintenance records and telephone (562) 627–5324; email
airworthy bearing and perform a new Instructions for Continued Galib.Abumeri@faa.gov.
reference measurement by following the Airworthiness (ICA). If the hours time- SUPPLEMENTARY INFORMATION:
requirements of paragraph (f)(6) of this AD. in-service (TIS) of a pin is unknown, or
if a pin has exceeded its life limit, this Comments Invited
(g) Alternative Methods of Compliance
(AMOCs) proposed AD would require removing We invite you to participate in this
(1) The Manager, Safety Management
the affected pin from service. This rulemaking by submitting written
Group, FAA, may approve AMOCs for this proposed AD is prompted by a report comments, data, or views. We also
AD. Send your proposal to: Matt Wilbanks, from an operator who purchased pins invite comments relating to the
Aviation Safety Engineer, Rotorcraft that did not have life limit economic, environmental, energy, or
Certification Office, Rotorcraft Directorate, documentation. The proposed actions federalism impacts that might result
FAA, 10101 Hillwood Pkwy, Fort Worth, are intended to document the life limit from adopting the proposals in this
Texas 76177; telephone (817) 222–5110; to prevent a pin remaining in service document. The most helpful comments
email 9-ASW-FTW-AMOC-Requests@faa.gov. beyond its fatigue life, which could
(2) For operations conducted under a 14 reference a specific portion of the
CFR part 119 operating certificate or under
result in failure of a pin, failure of a proposal, explain the reason for any
main rotor blade, and subsequent loss of recommended change, and include
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or control of the helicopter. supporting data. To ensure the docket
lacking a principal inspector, the manager of DATES: We must receive comments on does not contain duplicate comments,
the local flight standards district office or this proposed AD by November 2, 2015. commenters should send only one copy
certificate holding district office before ADDRESSES: You may send comments by of written comments, or if comments are
operating any aircraft complying with this filed electronically, commenters should
AD through an AMOC.
any of the following methods:
• Federal eRulemaking Docket: Go to submit only one time.
(h) Additional Information http://www.regulations.gov. Follow the We will file in the docket all
The subject of this AD is addressed in online instructions for sending your comments that we receive, as well as a
European Aviation Safety Agency (EASA) AD comments electronically. report summarizing each substantive
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Document Created: 2018-02-26 10:10:35
Document Modified: 2018-02-26 10:10:35
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by November 2, 2015. | |
| Contact | Matt Wilbanks, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, Texas 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 80 FR 53024 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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