81 FR 74362 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France)
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 207 (October 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 207 (October 26, 2016)
| Page Range | 74362-74364 | |
| FR Document | 2016-25748 |
[Federal Register Volume 81, Number 207 (Wednesday, October 26, 2016)] [Proposed Rules] [Pages 74362-74364] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-25748] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-3343; Directorate Identifier 2015-SW-078-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-12- 12 for Airbus Helicopters (previously Eurocopter France) Model EC130B4 and Model EC120B helicopters. AD 2014-12-12 currently requires inspecting and, if necessary, replacing parts of the sliding door star support attachment assembly. This proposed AD would expand the applicability and provide revised instructions for reinforcing the sliding door. These proposed actions are intended to prevent failure of the sliding door star support attachment, which could inhibit the operation of the sliding door from the inside, delaying the evacuation of passengers during an emergency. DATES: We must receive comments on this proposed AD by December 27, 2016. 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 by searching for and locating Docket No. FAA-2016- 3343; 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 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.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, TX 76177. FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5116; 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 [[Page 74363]] 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 June 13, 2014, we issued AD 2014-12-12, Amendment 39-17873 (79 FR 36638, June 30, 2014) for Airbus Helicopters Model EC120B helicopters with serial numbers up to and including 1367 and with a sliding door part number (P/N) C526A2370101 installed and Model EC130B4 helicopters with sliding door P/N C526S1101051 installed. AD 2014-12-12 does not apply to helicopters with modification (MOD) 07 3796 or 07 2921 installed. AD 2014-12-12 requires inspecting the upper and lower locking pin control rod fittings and the star support pin for a crack and reinforcing the sliding door star support stringer by installing three carbon fabric plies. AD 2014-12-12 was prompted by AD No. 2013-0093, dated April 15, 2013, and corrected on April 17, 2013, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA AD No. 2013-0093 was issued to correct an unsafe condition for Model EC120B and EC130B4 helicopters after a case was reported where passengers could not open a helicopter's sliding door after landing. EASA advises that an investigation revealed a failure of the sliding door star axle support. Actions Since AD 2014-12-12 Was Issued Since we issued AD 2014-12-12, EASA has issued EASA AD No. 2015- 0020, dated February 11, 2015, to correct an unsafe condition for Model EC120B helicopters with sliding door P/N C526A2370101 and Model EC130B4 helicopters sliding door P/N C526S1101051. EASA AD No. 2015-0020 does not apply to helicopters with MOD A00565, 07 3796, or 07 2921. EASA AD No. 2015-0020 supersedes EASA AD No. 2013-0093. EASA advises that after it issued AD No. 2013-0093, it discovered that the doors could be installed on all serial-numbered EC120B helicopters. Also, Eurocopter (now Airbus Helicopters) learned of difficulties with installing the angle bracket and plate used to reinforce the sliding door star support. Because of the distance between the star support pin and the bottom of the stringer on composite sliding doors, installation of the angle bracket and plate is not possible in a small number of sliding doors. Eurocopter subsequently revised its repair procedures to provide an alternate method for reinforcing the sliding door star support. EASA advises that it consequently issued AD No. 2015-0020 to extend the applicability to all serial-numbered EC120B helicopters with the affected sliding doors. EASA AD No. 2015-0020 also requires compliance with the revised service information. 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. Related Service Information Under 1 CFR Part 51 We reviewed Eurocopter (now Airbus Helicopters) Alert Service Bulletin (ASB) No. EC120-52A014, Revision 2, dated October 28, 2013, for Model EC120B helicopters and ASB No. 130-52A009, Revision 1, dated January 25, 2013, for Model EC130B4 helicopters. This service information specifies visual and dye penetrant inspections of sections of the sliding door attachment assembly and reinforcement of the sliding door star support. ASB EC120-52A014 was changed at Revision 2 to expand the applicability for all serial-numbered Model 120B helicopters and provides an alternative procedure for reinforcing the sliding door star support. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Proposed AD Requirements This proposed AD would require, within 165 hours time-in-service (TIS): Visually inspecting each upper and lower locking pin control rod end fitting (control end fitting) and replacing it before further flight if it is bent, twisted, or broken. Cleaning and dye-penetrant inspecting the star support pin for a crack and replacing it before further flight if it is cracked. Reinforcing the sliding door star support stringer by installing three carbon fabric plies. This proposed AD would also prohibit installing a sliding door P/N C526A2370101 on a Model EC120B helicopter, or a sliding door P/N C526S1101051 on a Model EC130B4 helicopter, unless the sliding door star support stringer is reinforced as required by this proposed AD. Costs of Compliance We estimate that this proposed AD would affect 261 helicopters of U.S. Registry and that labor costs average $85 a work hour. Based on these estimates, we expect the following costs: Visually inspecting the control rod end fittings would require 1 work-hour and a minimal amount for consumable materials for an estimated cost of $85 per helicopter, or $22,185 for the U.S. fleet. Replacing the control rod end fittings with airworthy fittings would require 5 work-hours for a labor cost of $425. Parts would cost about $242 for an estimated total cost of $667 per helicopter. Dye-penetrant inspecting the star support pin for a crack would require 2 work-hours and no parts for an estimated cost of $170 per helicopter and $44,370 for the U.S. fleet. Replacing the star support pin would require 5 work-hours. Parts would cost about $200 for an estimated total cost of $625 per helicopter. Installing three carbon fabric plies to reinforce the sliding door star support would require 5 work-hours. Parts would cost $200 for an estimated total cost of $625 per helicopter and $163,125 for the U.S. fleet. 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, [[Page 74364]] 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) 2014-12-12, Amendment 39-17873 (79 FR 36638, June 30, 2014), and adding the following new AD: Airbus Helicopters (Previously Eurocopter France): Docket No. FAA- 2016-3343; Directorate Identifier 2015-SW-078-AD. (a) Applicability This AD applies to the following helicopters, certificated in any category, except those with modification A00565, 07 3796, or 07 2921 installed: (1) Model EC120B helicopters with a sliding door part number (P/ N) C526A2370101 installed; and (2) Model EC130B4 helicopters with a sliding door P/N C526S1101051 installed. (b) Unsafe Condition This AD defines the unsafe condition as a failure of the sliding door star axle support. This condition could prevent operation of a sliding door from inside, which could delay evacuation of passengers during an emergency. (c) Affected ADs This AD supersedes AD 2014-12-12, Amendment 39-17873 (79 FR 36638, June 30, 2014). (d) Comments Due Date We must receive comments by December 27, 2016. (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) Within 165 hours time-in-service: (i) Visually inspect each upper and lower locking pin control rod end fitting (control end fitting) for a bend, twist, or breakage. If a control end fitting is bent, twisted, or broken, before further flight, replace the control end fitting with an airworthy control end fitting. (ii) Clean and dye penetrant inspect the star support pin for a crack in the areas identified as Zone X and Zone Y in Figure 3 of Eurocopter Alert Service Bulletin No. EC120-52A014, Revision 2, dated October 28, 2013 (ASB No. EC120-52A014) or Eurocopter Alert Service Bulletin No. EC130-52A009, Revision 1, dated January 25, 2013 (ASB No. EC130-52A009), as applicable to your model helicopter. If there is a crack in the star support pin, before further flight, replace the star support pin with an airworthy star support pin. (iii) Reinforce the sliding door star support stringer by installing three carbon fiber plies and re-identify the sliding door by following the Accomplishment Instructions, paragraphs 3.B.2.d. and 3.B.2.e of ASB No. EC120-52A014, or paragraph 3.B.2.d. and the table under paragraph 3.C of ASB No. EC130-52A009, whichever is applicable to your model helicopter. (2) After the effective date of this AD, do not install a sliding door P/N C526A2370101 on an EC120B helicopter, or a sliding door P/N C526S1101051 on an EC130B4 helicopter, unless the sliding door has been reinforced as required by paragraph (f)(1)(iii) of this AD. (g) Credit for Actions Previously Completed Compliance with AD 2014-12-12 (79 FR 366838, June 30, 2014) before the effective date of this AD is considered acceptable for compliance with the corresponding actions specified in paragraph (f)(1) of this AD. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222- 5116; 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. (i) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015-0020, dated February 11, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2016-3343. (j) Subject Joint Aircraft Service Component (JASC) Code: 5220, Emergency Exits. Issued in Fort Worth, Texas, on October 18, 2016. James A. Grigg, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-25748 Filed 10-25-16; 8:45 am] BILLING CODE 4910-13-P
![74362 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
any category, serial numbers 003 through 672 (TCCA); or Bombardier, Inc.’s TCCA Design DATES: We must receive comments on
inclusive, on which Bombardier ModSum Approval Organization (DAO). If approved by this proposed AD by December 27,
8Q100813 or Bombardier Service Bulletin 8– the DAO, the approval must include the 2016.
74–02 is incorporated. DAO-authorized signature.
(1) Model DHC–8–102, –103, and –106 ADDRESSES: You may send comments by
(j) Related Information
airplanes. any of the following methods:
(2) Model DHC–8–201 and –202 airplanes. (1) Refer to Mandatory Continuing • Federal eRulemaking Docket: Go to
(3) Model DHC–8–301, –311, and –315 Airworthiness Information (MCAI) Canadian http://www.regulations.gov. Follow the
airplanes. Airworthiness Directive CF–2013–36, dated online instructions for sending your
November 19, 2013, for related information.
(d) Subject This MCAI may be found in the AD docket
comments electronically.
Air Transport Association (ATA) of on the Internet at http://www.regulations.gov • Fax: 202–493–2251.
America Code 74, Ignition. by searching for and locating Docket No. • Mail: Send comments to the U.S.
FAA–2016–9299. Department of Transportation, Docket
(e) Reason Operations, M–30, West Building
(2) For service information identified in
This AD was prompted by reports of this AD, contact Bombardier, Inc., Q-Series Ground Floor, Room W12–140, 1200
incorrect installation of the auto-ignition Technical Help Desk, 123 Garratt Boulevard, New Jersey Avenue SE., Washington,
system due to crossed wires at one of the Toronto, Ontario M3K 1Y5, Canada; DC 20590–0001.
splices in the auto-relight system. We are telephone 416–375–4000; fax 416–375–4539; • Hand Delivery: Deliver to the
issuing this AD to detect and correct email thd.qseries@aero.bombardier.com;
incorrect wiring of the auto-ignition system,
‘‘Mail’’ address between 9 a.m. and 5
Internet http://www.bombardier.com. You
which could result in inability to restart the p.m., Monday through Friday, except
may view this service information at the
engine in flight and consequent reduced FAA, Transport Airplane Directorate, 1601 Federal holidays.
controllability of the airplane. Lind Avenue SW., Renton, WA. For Examining the AD Docket
(f) Compliance information on the availability of this
material at the FAA, call 425–227–1221. You may examine the AD docket on
Comply with this AD within the the Internet at http://
compliance times specified, unless already Issued in Renton, Washington, on October
14, 2016.
www.regulations.gov by searching for
done. and locating Docket No. FAA–2016–
Michael Kaszycki,
(g) Inspection and Corrective Actions 3343; or in person at the Docket
Acting Manager, Transport Airplane Operations Office between 9 a.m. and 5
Within 2,000 flight hours or 12 months Directorate, Aircraft Certification Service.
after the effective date of this AD, whichever p.m., Monday through Friday, except
occurs first: Inspect the auto-ignition system [FR Doc. 2016–25664 Filed 10–25–16; 8:45 am] Federal holidays. The AD docket
for correct wiring and do all applicable BILLING CODE 4910–13–P contains this proposed AD, the
corrective actions, in accordance with the European Aviation Safety Agency
Accomplishment Instructions of Bombardier (EASA) AD, the economic evaluation,
Service Bulletin 8–74–05, Revision B, dated DEPARTMENT OF TRANSPORTATION
April 14, 2014. All applicable corrective
any comments received and other
actions must be done before further flight. Federal Aviation Administration information. The street address for the
Docket Operations Office (telephone
(h) Credit for Previous Actions 800–647–5527) is in the ADDRESSES
14 CFR Part 39
This paragraph provides credit for the section. Comments will be available in
actions required by paragraph (g) of this AD, [Docket No. FAA–2016–3343; Directorate the AD docket shortly after receipt.
if those actions were performed before the Identifier 2015–SW–078–AD] For service information identified in
effective date of this AD using Bombardier this proposed rule, contact Airbus
Service Bulletin 8–74–05, dated July 12, RIN 2120–AA64
2013; or Revision A, dated January 27, 2014. Helicopters, 2701 N. Forum Drive,
Airworthiness Directives; Airbus Grand Prairie, TX 75052; telephone
(i) Other FAA AD Provisions Helicopters (Previously Eurocopter (972) 641–0000 or (800) 232–0323; fax
The following provisions also apply to this France) (972) 641–3775; or at http://
AD: www.airbushelicopters.com/techpub.
(1) Alternative Methods of Compliance AGENCY: Federal Aviation You may review service information at
(AMOCs): The Manager, New York ACO, Administration (FAA), DOT. the FAA, Office of the Regional Counsel,
ANE–170, FAA, has the authority to approve ACTION: Notice of proposed rulemaking
AMOCs for this AD, if requested using the
Southwest Region, 10101 Hillwood
(NPRM). Pkwy., Room 6N–321, Fort Worth, TX
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your SUMMARY: We propose to supersede 76177.
request to your principal inspector or local Airworthiness Directive (AD) 2014–12– FOR FURTHER INFORMATION CONTACT:
Flight Standards District Office, as 12 for Airbus Helicopters (previously David Hatfield, Aviation Safety
appropriate. If sending information directly
Eurocopter France) Model EC130B4 and Engineer, Safety Management Group,
to the ACO, send it to ATTN: Program
Manager, Continuing Operational Safety, Model EC120B helicopters. AD 2014– Rotorcraft Directorate, FAA, 10101
FAA, New York ACO, 1600 Stewart Avenue, 12–12 currently requires inspecting and, Hillwood Pkwy., Fort Worth, TX 76177;
Suite 410, Westbury, NY 11590; telephone if necessary, replacing parts of the telephone (817) 222–5116; email
516–228–7300; fax 516–794–5531. Before sliding door star support attachment david.hatfield@faa.gov.
using any approved AMOC, notify your assembly. This proposed AD would SUPPLEMENTARY INFORMATION:
appropriate principal inspector, or lacking a expand the applicability and provide
principal inspector, the manager of the local revised instructions for reinforcing the Comments Invited
Lhorne on DSK30JT082PROD with PROPOSALS
flight standards district office/certificate sliding door. These proposed actions are We invite you to participate in this
holding district office.
intended to prevent failure of the sliding rulemaking by submitting written
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective door star support attachment, which comments, data, or views. We also
actions from a manufacturer, the action must could inhibit the operation of the invite comments relating to the
be accomplished using a method approved sliding door from the inside, delaying economic, environmental, energy, or
by the Manager, New York ACO, ANE–170, the evacuation of passengers during an federalism impacts that might result
FAA; or Transport Canada Civil Aviation emergency. from adopting the proposals in this
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![74364 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
Part A, Subpart III, Section 44701: Airbus Helicopters (Previously Eurocopter (g) Credit for Actions Previously Completed
General requirements.’’ Under that France): Docket No. FAA–2016–3343; Compliance with AD 2014–12–12 (79 FR
section, Congress charges the FAA with Directorate Identifier 2015–SW–078–AD. 366838, June 30, 2014) before the effective
promoting safe flight of civil aircraft in (a) Applicability date of this AD is considered acceptable for
air commerce by prescribing regulations compliance with the corresponding actions
This AD applies to the following specified in paragraph (f)(1) of this AD.
for practices, methods, and procedures helicopters, certificated in any category,
the Administrator finds necessary for except those with modification A00565, 07 (h) Alternative Methods of Compliance
safety in air commerce. This regulation 3796, or 07 2921 installed: (AMOCs)
is within the scope of that authority (1) Model EC120B helicopters with a (1) The Manager, Safety Management
because it addresses an unsafe condition sliding door part number (P/N) Group, FAA, may approve AMOCs for this
that is likely to exist or develop on C526A2370101 installed; and AD. Send your proposal to: David Hatfield,
products identified in this rulemaking (2) Model EC130B4 helicopters with a Aviation Safety Engineer, Safety Management
action. sliding door P/N C526S1101051 installed. Group, Rotorcraft Directorate, FAA, 10101
(b) Unsafe Condition Hillwood Pkwy., Fort Worth, TX 76177;
Regulatory Findings telephone (817) 222–5116; email 9-ASW-
This AD defines the unsafe condition as a FTW-AMOC-Requests@faa.gov.
We determined that this proposed AD failure of the sliding door star axle support. (2) For operations conducted under a 14
would not have federalism implications This condition could prevent operation of a CFR part 119 operating certificate or under
under Executive Order 13132. This sliding door from inside, which could delay 14 CFR part 91, subpart K, we suggest that
proposed AD would not have a evacuation of passengers during an you notify your principal inspector, or
substantial direct effect on the States, on emergency. lacking a principal inspector, the manager of
the relationship between the national (c) Affected ADs the local flight standards district office or
Government and the States, or on the certificate holding district office before
This AD supersedes AD 2014–12–12, operating any aircraft complying with this
distribution of power and Amendment 39–17873 (79 FR 36638, June
responsibilities among the various AD through an AMOC.
30, 2014).
levels of government. (i) Additional Information
For the reasons discussed, I certify (d) Comments Due Date
The subject of this AD is addressed in
this proposed regulation: We must receive comments by December European Aviation Safety Agency (EASA) AD
1. Is not a ‘‘significant regulatory 27, 2016. No. 2015–0020, dated February 11, 2015. You
action’’ under Executive Order 12866; (e) Compliance may view the EASA AD on the Internet at
2. Is not a ‘‘significant rule’’ under the http://www.regulations.gov in Docket No.
You are responsible for performing each FAA–2016–3343.
DOT Regulatory Policies and Procedures
action required by this AD within the
(44 FR 11034, February 26, 1979); specified compliance time unless it has (j) Subject
3. Will not affect intrastate aviation in already been accomplished prior to that time. Joint Aircraft Service Component (JASC)
Alaska to the extent that it justifies Code: 5220, Emergency Exits.
making a regulatory distinction; and (f) Required Actions
4. Will not have a significant (1) Within 165 hours time-in-service: Issued in Fort Worth, Texas, on October 18,
economic impact, positive or negative, (i) Visually inspect each upper and lower 2016.
on a substantial number of small entities locking pin control rod end fitting (control James A. Grigg,
under the criteria of the Regulatory end fitting) for a bend, twist, or breakage. If Acting Manager, Rotorcraft Directorate,
a control end fitting is bent, twisted, or Aircraft Certification Service.
Flexibility Act.
broken, before further flight, replace the [FR Doc. 2016–25748 Filed 10–25–16; 8:45 am]
We prepared an economic evaluation control end fitting with an airworthy control
of the estimated costs to comply with end fitting. BILLING CODE 4910–13–P
this proposed AD and placed it in the (ii) Clean and dye penetrant inspect the
AD docket. star support pin for a crack in the areas
identified as Zone X and Zone Y in Figure DEPARTMENT OF HEALTH AND
List of Subjects in 14 CFR Part 39 3 of Eurocopter Alert Service Bulletin No. HUMAN SERVICES
Air transportation, Aircraft, Aviation EC120–52A014, Revision 2, dated October
safety, Incorporation by reference, 28, 2013 (ASB No. EC120–52A014) or Food and Drug Administration
Safety. Eurocopter Alert Service Bulletin No. EC130–
52A009, Revision 1, dated January 25, 2013
The Proposed Amendment 21 CFR Part 2
(ASB No. EC130–52A009), as applicable to
your model helicopter. If there is a crack in [Docket No. FDA–2015–N–1355]
Accordingly, under the authority
the star support pin, before further flight,
delegated to me by the Administrator, replace the star support pin with an RIN 0910–AH36
the FAA proposes to amend 14 CFR part airworthy star support pin.
39 as follows: (iii) Reinforce the sliding door star support Use of Ozone-Depleting Substances
stringer by installing three carbon fiber plies
PART 39—AIRWORTHINESS and re-identify the sliding door by following AGENCY: Food and Drug Administration,
DIRECTIVES the Accomplishment Instructions, paragraphs HHS.
3.B.2.d. and 3.B.2.e of ASB No. EC120– ACTION: Proposed rule.
■ 1. The authority citation for part 39 52A014, or paragraph 3.B.2.d. and the table
continues to read as follows: under paragraph 3.C of ASB No. EC130– SUMMARY: The Food and Drug
52A009, whichever is applicable to your Administration (FDA, the Agency, or
Lhorne on DSK30JT082PROD with PROPOSALS
Authority: 49 U.S.C. 106(g), 40113, 44701.
model helicopter. we) is proposing to amend its regulation
§ 39.13 [Amended] (2) After the effective date of this AD, do
on uses of ozone-depleting substances
not install a sliding door P/N C526A2370101
■ 2. The FAA amends § 39.13 by on an EC120B helicopter, or a sliding door (ODSs), including chlorofluorocarbons
removing Airworthiness Directive (AD) P/N C526S1101051 on an EC130B4 (CFCs), to remove the designation for
2014–12–12, Amendment 39–17873 (79 helicopter, unless the sliding door has been certain products as ‘‘essential uses’’
FR 36638, June 30, 2014), and adding reinforced as required by paragraph (f)(1)(iii) under the Clean Air Act. Essential-use
the following new AD: of this AD. products are exempt from the ban by
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Document Created: 2016-10-26 02:17:49
Document Modified: 2016-10-26 02:17:49
| 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 December 27, 2016. | |
| Contact | David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5116; email [email protected] | |
| FR Citation | 81 FR 74362 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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