80 FR 43645 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 141 (July 23, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 141 (July 23, 2015)
| Page Range | 43645-43647 | |
| FR Document | 2015-17952 |
[Federal Register Volume 80, Number 141 (Thursday, July 23, 2015)] [Proposed Rules] [Pages 43645-43647] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-17952] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2568; Directorate Identifier 2014-SW-026-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede airworthiness directive (AD) 2014-07- 52 for certain Airbus Helicopters (previously Eurocopter France) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2014-07-52 currently requires repetitively inspecting certain reinforcement angles of the rear structure to tailboom junction frame (reinforcement angles) for a crack at 10 hour time-in-service (TIS) intervals, repairing any cracked reinforcement angle, and allows an optional repetitive inspection with a 165 hour TIS inspection interval as a terminating action for the 10 hour TIS inspections. This proposed AD would retain the inspection requirements of AD 2014-07-52 and require the inspection of the area around each reinforcement angle screw hole as terminating action to the 10 hour TIS inspections. These proposed actions are intended to detect a crack in the reinforcement angle, which if not corrected, could result in loss of the tailboom and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by September 21, 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, TX 76177. FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 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 May 21, 2014, we issued AD 2014-07-52, Amendment 39-17858, 79 FR 33054, June 10, 2014) for Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with Modification (MOD) 07 3215 installed or with a reinforcement angle, part-number (P/ N) 350A08.2493.21 or 350A08.2493.23, installed. AD 2014-07-52 requires, for helicopters with 640 or more hours TIS, within 10 hours TIS and thereafter at [[Page 43646]] intervals not exceeding 10 hours TIS, repetitively inspecting each reinforcement angle for a crack. If there is a crack, AD 2014-07-52 requires, before further flight, repairing the reinforcement angle. As an optional terminating action for the repetitive 10 hour TIS inspections, AD 2014-07-52 allows a repetitive 165 hour TIS inspection of the reinforcement angle under each attaching screw for a crack. AD 2014-07-52 was prompted by Emergency AD No. 2014-0076-E, dated March 25, 2014, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Helicopters Model AS350B, AS350BA, AS350BB, AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters with MOD 07 3215 or with at least one reinforcement angle, P/N 350A08.2493.21 or P/N 350A08.2493.23, installed. EASA advises that during the inspection of several AS355 helicopters, cracks found in the reinforcement angles had initiated on the non-visible surface of the angle, and that this condition, if not corrected, could lead to further crack propagation and subsequent loss of the tailboom, resulting in loss of control of the helicopter. The EASA AD requires repetitive inspections of the reinforcement angles, and states that a terminating action is under investigation. Actions Since AD 2014-07-52 Was Issued Since we issued AD 2014-07-52 (79 FR 33054, June 10, 2014), we have determined that the optional terminating action in AD 2014-07-52 should be a required terminating action. This NPRM would retain the actions in AD 2014-07-52 but would require the 165-hour TIS visual inspection as terminating action for the 10-hour TIS inspections. In addition, because MOD 07 3215 installed reinforcement angle P/Ns 350A08.2493.21 and 350A08.2493.23, AD 2014-07-52 was written to apply to helicopters with either the reinforcement angle P/Ns or with MOD 07 3215, so that operators could more easily determine whether AD 2014-07-52 applied to their aircraft. Airbus Helicopters then developed MOD 07 3232, which removes reinforcement angle P/N 350A08.2493.21 and P/N 350A08.2493.23. Because a helicopter with both MOD 07 3215 and MOD 07 3232 in its aircraft records would not have reinforcement angle P/N 350A08.2493.21 or P/N 350A08.2493.23 installed, this NPRM would revise the applicability to no longer include helicopters with MOD 07 3215 and to include a note clarifying that the AD would not apply if MOD 07 3232 is installed. Comments After AD 2014-07-52 (79 FR 33054, June 10, 2014), was published, we received comments from three commenters. Request Two commenters requested that the AD not be applicable to aircraft with MOD 07 3232 installed, as this modification improved the attachment at the junction frame to prevent cracking. We partially agree. Although AD 2014-07-52 does not apply to helicopters with MOD 07 3232 installed, we have revised the language in the proposed AD so that this exclusion is more clear. Two commenters requested that we increase the time between inspections or allow the repetitive inspections to end if no cracks are found after a few inspections. The commenters stated that the inspection frequency of the repetitive 165-hour TIS inspection is excessive and that if correctly installed, the doublers do not crack. One commenter stated that in practice the 165-hour inspection is being completed at every 100-hour inspection to avoid repeated grounding of the aircraft. Another commenter stated that frequent removal of the bolts and nuts could affect the airworthiness of the aircraft. We do not agree. Analysis has demonstrated that cracking has been found in more than one location, which indicates there may be more than one cause of the cracking. The uncertainty regarding the root cause of the cracking supports requiring the 165-hour TIS inspections without any changes. 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 Airbus Helicopters issued Emergency Alert Service Bulletin (EASB) No. 05.00.70 for Model AS350B, BA, BB, Bl, B2, B3, and D helicopters and EASB No. 05.00.62 for Model AS355E, F, F1, F2, N, and NP helicopters, both Revision 0 and dated March 24, 2014. EASB No. 05.00.70 and EASB No. 05.00.62 describe procedures for inspecting the angle reinforcements for a crack. 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 retain the 10 hour TIS repetitive inspection of the junction frame required by AD 2014-07-52 (79 FR 33054, June 10, 2014), and would also require the repetitive 165 hour TIS inspection of the junction frame bores as a terminating action for the 10 hour TIS inspection. This proposed AD would also revise the applicability paragraph by no longer including helicopters with MOD 07 3215. Differences Between This Proposed AD and the EASA AD This proposed AD is not applicable to the AS350BB as that model is not type certificated in the U.S. This proposed AD applies to Airbus Helicopters Model AS350C and AS350D1 helicopters because these helicopters have a similar design. Finally, the EASA AD requires operators to contact Airbus Helicopters if there is a crack, and this proposed AD does not, however it does require repairing the crack before further flight. Interim Action We consider this proposed AD to be an interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this proposed AD would affect 822 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this proposed AD. At an average labor rate of $85 per hour, inspecting the reinforcement angles for a crack without removing the screws would require 1.0 work-hour, for a cost per helicopter of $85 and a total cost of $69,870 for the U.S. fleet per inspection cycle. Removing the screws and inspecting the reinforcement angle would require 2 work-hours, for a cost per helicopter of $170 and a total cost of $139,740 for the U.S. fleet, per inspection cycle. If required, repairing a cracked reinforcement angle would require about 10 work-hours, and [[Page 43647]] required parts would cost about $300, for a total cost per helicopter of $1,150. 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) 2014-07052, Amendment 39-17858 (79 FR 33054, June 10, 2014), and adding the following new AD: Airbus Helicopters (previously Eurocopter France): Docket No. FAA- 2015-2568; Directorate Identifier 2014-SW-026-AD. (a) Applicability This AD applies to Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, with a reinforcement angle part number (P/N) 350A08.2493.21 or P/N 350A08.2493.23 installed, certificated in any category. Note 1 to paragraph (a) of this AD: Helicopters with Modification (MOD) 073232 do not have P/N 350A08.2493.21 or P/N 350A08.2493.23 installed. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a rear structure to tailboom junction frame reinforcement angle (reinforcement angle), which if not detected could result in loss of the tail boom and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2014-07-52, Amendment 39-17858 (79 FR 33054, June 10, 2014). (d) Comments Due Date We must receive comments by September 21, 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) For helicopters with 640 or more hours time-in-service (TIS) since installation of MOD 07 3215 or since installation of an applicable reinforcement angle, within 10 hours TIS, and thereafter at intervals not exceeding 10 hours TIS, inspect each reinforcement angle for a crack as depicted in Figure 1 of Airbus Helicopters Emergency Alert Service Bulletin No. 05.00.70 for Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, and AS350D1 helicopters and Airbus Helicopters Emergency Alert Service Bulletin No. 05.00.62 for AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, both Revision 0 and dated March 24, 2014. (2) If there is a crack, before further flight, repair the reinforcement angle in a manner approved by the manager listed in paragraph (h)(1) of this AD. (3) Within 165 hours TIS after the first inspection required by paragraph (f)(1) of this AD, and thereafter at intervals not exceeding 165 hours TIS, remove screw No. 5 from the reinforcement angle, thoroughly clean the area around the hole and inspect the reinforcement angle for a crack. If there is not a crack, reinstall the screw. Sequentially repeat the steps required by this paragraph for screws No. 6 through No. 12. If there is a crack, comply with paragraph (f)(2) of this AD. Accomplishment of the inspection required by this paragraph terminates the repetitive inspections required by paragraph (f)(1) of this AD. (g) Special Flight Permit Special flight permits are prohibited. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, 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. (3) AMOCs approved previously in accordance with AD 2014-07-52, Amendment 39-17858 (79 FR 33054, June 10, 2014) are approved as AMOCs for the corresponding requirements of paragraph (f)(2) of this AD. (i) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD 2014-0076-E, dated March 25, 2014. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-2568. (j) Subject Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft Tailboom. Issued in Fort Worth, Texas, on July 15, 2015. Bruce E. Cain, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-17952 Filed 7-22-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 43645
required by this AD if it is approved by the SUMMARY: We propose to supersede For service information identified in
Boeing Commercial Airplanes Organization airworthiness directive (AD) 2014–07– this proposed AD, contact Airbus
Designation Authorization (ODA) that has 52 for certain Airbus Helicopters Helicopters, Inc., 2701 N. Forum Drive,
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
(previously Eurocopter France) Model Grand Prairie, TX 75052; telephone
method to be approved, the repair must meet AS350B, AS350BA, AS350B1, (972) 641–0000 or (800) 232–0323; fax
the certification basis of the airplane, and the AS350B2, AS350B3, AS350C, AS350D, (972) 641–3775; or at http://
approval must specifically refer to this AD. AS350D1, AS355E, AS355F, AS355F1, www.airbushelicopters.com/techpub.
(4) For service information that contains AS355F2, AS355N, and AS355NP You may review service information at
steps that are labeled as Required for helicopters. AD 2014–07–52 currently the FAA, Office of the Regional Counsel,
Compliance (RC), the provisions of requires repetitively inspecting certain Southwest Region, 10101 Hillwood
paragraphs (i)(4)(i) and (i)(4)(ii) apply.
reinforcement angles of the rear Pkwy., Room 6N–321, Fort Worth, TX
(i) The steps labeled as RC, including
substeps under an RC step and any figures structure to tailboom junction frame 76177.
identified in an RC step, must be done to (reinforcement angles) for a crack at 10 FOR FURTHER INFORMATION CONTACT:
comply with the AD. An AMOC is required hour time-in-service (TIS) intervals, Robert Grant, Aviation Safety Engineer,
for any deviations to RC steps, including repairing any cracked reinforcement Safety Management Group, FAA, 10101
substeps and identified figures. angle, and allows an optional repetitive
(ii) Steps not labeled as RC may be Hillwood Pkwy., Fort Worth, TX 76177;
inspection with a 165 hour TIS telephone (817) 222–5110; email
deviated from using accepted methods in inspection interval as a terminating
accordance with the operator’s maintenance robert.grant@faa.gov.
or inspection program without obtaining action for the 10 hour TIS inspections.
SUPPLEMENTARY INFORMATION:
approval of an AMOC, provided the RC steps, This proposed AD would retain the
including substeps and identified figures, can inspection requirements of AD 2014– Comments Invited
still be done as specified, and the airplane 07–52 and require the inspection of the We invite you to participate in this
can be put back in an airworthy condition. area around each reinforcement angle rulemaking by submitting written
(j) Related Information screw hole as terminating action to the comments, data, or views. We also
10 hour TIS inspections. These invite comments relating to the
(1) For more information about this AD,
contact Melanie Violette, Senior Aerospace proposed actions are intended to detect economic, environmental, energy, or
Engineer, Airframe Branch, ANM–120S, a crack in the reinforcement angle, federalism impacts that might result
FAA, Seattle Aircraft Certification Office which if not corrected, could result in from adopting the proposals in this
(ACO), 1601 Lind Avenue SW., Renton, WA loss of the tailboom and subsequent loss document. The most helpful comments
98057–3356; phone: 425–917–6422; fax: 425– of control of the helicopter.
917–6590; email: melanie.violette@faa.gov. reference a specific portion of the
(2) For service information identified in DATES: We must receive comments on proposal, explain the reason for any
this AD, contact Boeing Commercial this proposed AD by September 21, recommended change, and include
Airplanes, Attention: Data & Services 2015. supporting data. To ensure the docket
Management, P.O. Box 3707, MC 2H–65,
ADDRESSES: You may send comments by does not contain duplicate comments,
Seattle, WA 98124–2207; telephone 206– commenters should send only one copy
544–5000, extension 1; fax 206–766–5680; any of the following methods:
of written comments, or if comments are
Internet https://www.myboeingfleet.com. You • Federal eRulemaking Docket: Go to
filed electronically, commenters should
may view this referenced service information http://www.regulations.gov. Follow the
at the FAA, Transport Airplane Directorate, submit only one time.
online instructions for sending your We will file in the docket all
1601 Lind Avenue SW., Renton, WA. For comments electronically.
information on the availability of this comments that we receive, as well as a
material at the FAA, call 425–227–1221.
• Fax: 202–493–2251. report summarizing each substantive
• Mail: Send comments to the U.S. public contact with FAA personnel
Issued in Renton, Washington, on July 14, Department of Transportation, Docket
2015. concerning this proposed rulemaking.
Operations, M–30, West Building Before acting on this proposal, we will
Suzanne Masterson,
Ground Floor, Room W12–140, 1200 consider all comments we receive on or
Acting Manager, Transport Airplane New Jersey Avenue SE., Washington,
Directorate, Aircraft Certification Service. before the closing date for comments.
DC 20590–0001. We will consider comments filed after
[FR Doc. 2015–17955 Filed 7–22–15; 8:45 am]
• Hand Delivery: Deliver to the the comment period has closed if it is
BILLING CODE 4910–13–P
‘‘Mail’’ address between 9 a.m. and 5 possible to do so without incurring
p.m., Monday through Friday, except expense or delay. We may change this
Federal holidays. proposal in light of the comments we
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket receive.
Federal Aviation Administration Discussion
You may examine the AD docket on
14 CFR Part 39 the Internet at http:// On May 21, 2014, we issued AD
www.regulations.gov or in person at the 2014–07–52, Amendment 39–17858, 79
[Docket No. FAA–2015–2568; Directorate Docket Operations Office between 9 FR 33054, June 10, 2014) for Airbus
Identifier 2014–SW–026–AD] a.m. and 5 p.m., Monday through Helicopters Model AS350B, AS350BA,
RIN 2120–AA64 Friday, except Federal holidays. The AD AS350B1, AS350B2, AS350B3, AS350C,
docket contains this proposed AD, the AS350D, AS350D1, AS355E, AS355F,
mstockstill on DSK4VPTVN1PROD with PROPOSALS
Airworthiness Directives; Airbus European Aviation Safety Agency AS355F1, AS355F2, AS355N, and
Helicopters (Previously Eurocopter (EASA) AD, the economic evaluation, AS355NP helicopters with Modification
France) Helicopters any comments received and other (MOD) 07 3215 installed or with a
AGENCY: Federal Aviation information. The street address for the reinforcement angle, part-number (P/N)
Administration (FAA), DOT. Docket Operations Office (telephone 350A08.2493.21 or 350A08.2493.23,
800–647–5527) is in the ADDRESSES installed. AD 2014–07–52 requires, for
ACTION: Notice of proposed rulemaking
section. Comments will be available in helicopters with 640 or more hours TIS,
(NPRM).
the AD docket shortly after receipt. within 10 hours TIS and thereafter at
VerDate Sep<11>2014 19:18 Jul 22, 2015 Jkt 235001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\23JYP1.SGM 23JYP1](https://thefederalregister.org/doc/80_FR_43786/page/1.svg)
![Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 43647
required parts would cost about $300, PART 39—AIRWORTHINESS approved by the manager listed in paragraph
for a total cost per helicopter of $1,150. DIRECTIVES (h)(1) of this AD.
(3) Within 165 hours TIS after the first
Authority for This Rulemaking ■ 1. The authority citation for part 39 inspection required by paragraph (f)(1) of this
Title 49 of the United States Code continues to read as follows: AD, and thereafter at intervals not exceeding
specifies the FAA’s authority to issue Authority: 49 U.S.C. 106(g), 40113, 44701. 165 hours TIS, remove screw No. 5 from the
rules on aviation safety. Subtitle I, reinforcement angle, thoroughly clean the
section 106, describes the authority of § 39.13 [Amended] area around the hole and inspect the
the FAA Administrator. ‘‘Subtitle VII: ■ 2. The FAA amends § 39.13 by reinforcement angle for a crack. If there is not
Aviation Programs,’’ describes in more removing Airworthiness Directive (AD) a crack, reinstall the screw. Sequentially
detail the scope of the Agency’s 2014–07052, Amendment 39–17858 (79 repeat the steps required by this paragraph
authority. FR 33054, June 10, 2014), and adding for screws No. 6 through No. 12. If there is
We are issuing this rulemaking under the following new AD: a crack, comply with paragraph (f)(2) of this
the authority described in ‘‘Subtitle VII, AD. Accomplishment of the inspection
Airbus Helicopters (previously Eurocopter
Part A, Subpart III, Section 44701: France): Docket No. FAA–2015–2568; required by this paragraph terminates the
General requirements.’’ Under that Directorate Identifier 2014–SW–026–AD. repetitive inspections required by paragraph
section, Congress charges the FAA with (f)(1) of this AD.
(a) Applicability
promoting safe flight of civil aircraft in (g) Special Flight Permit
This AD applies to Airbus Helicopters
air commerce by prescribing regulations
Model AS350B, AS350BA, AS350B1, Special flight permits are prohibited.
for practices, methods, and procedures AS350B2, AS350B3, AS350C, AS350D,
the Administrator finds necessary for AS350D1, AS355E, AS355F, AS355F1, (h) Alternative Methods of Compliance
safety in air commerce. This regulation AS355F2, AS355N, and AS355NP (AMOCs)
is within the scope of that authority helicopters, with a reinforcement angle part (1) The Manager, Safety Management
because it addresses an unsafe condition number (P/N) 350A08.2493.21 or P/N Group, FAA, may approve AMOCs for this
that is likely to exist or develop on 350A08.2493.23 installed, certificated in any AD. Send your proposal to: Robert Grant,
products identified in this rulemaking category.
Aviation Safety Engineer, Safety Management
action. Note 1 to paragraph (a) of this AD: Group, FAA, 10101 Hillwood Pkwy., Fort
Helicopters with Modification (MOD) 073232
Regulatory Findings Worth, TX 76177; telephone (817) 222–5110;
do not have P/N 350A08.2493.21 or P/N
350A08.2493.23 installed. email robert.grant@faa.gov.
We determined that this proposed AD (2) For operations conducted under a 14
would not have federalism implications (b) Unsafe Condition CFR part 119 operating certificate or under
under Executive Order 13132. This This AD defines the unsafe condition as a 14 CFR part 91, subpart K, we suggest that
proposed AD would not have a crack in a rear structure to tailboom junction you notify your principal inspector, or
substantial direct effect on the States, on frame reinforcement angle (reinforcement lacking a principal inspector, the manager of
the relationship between the national angle), which if not detected could result in the local flight standards district office or
Government and the States, or on the loss of the tail boom and subsequent loss of certificate holding district office before
distribution of power and control of the helicopter. operating any aircraft complying with this
responsibilities among the various (c) Affected ADs AD through an AMOC.
levels of government. This AD supersedes AD 2014–07–52, (3) AMOCs approved previously in
For the reasons discussed, I certify Amendment 39–17858 (79 FR 33054, June accordance with AD 2014–07–52,
this proposed regulation: 10, 2014). Amendment 39–17858 (79 FR 33054, June
1. Is not a ‘‘significant regulatory 10, 2014) are approved as AMOCs for the
action’’ under Executive Order 12866; (d) Comments Due Date corresponding requirements of paragraph
2. Is not a ‘‘significant rule’’ under the We must receive comments by September (f)(2) of this AD.
DOT Regulatory Policies and Procedures 21, 2015.
(i) Additional Information
(44 FR 11034, February 26, 1979); (e) Compliance
3. Will not affect intrastate aviation in The subject of this AD is addressed in
You are responsible for performing each
Alaska to the extent that it justifies European Aviation Safety Agency (EASA) AD
action required by this AD within the
making a regulatory distinction; and specified compliance time unless it has 2014–0076–E, dated March 25, 2014. You
4. Will not have a significant already been accomplished prior to that time. may view the EASA AD on the Internet at
economic impact, positive or negative, http://www.regulations.gov in Docket No.
(f) Required Actions FAA–2015–2568.
on a substantial number of small entities
under the criteria of the Regulatory (1) For helicopters with 640 or more hours
time-in-service (TIS) since installation of (j) Subject
Flexibility Act.
MOD 07 3215 or since installation of an Joint Aircraft Service Component (JASC)
We prepared an economic evaluation applicable reinforcement angle, within 10 Code: 5302: Rotorcraft Tailboom.
of the estimated costs to comply with hours TIS, and thereafter at intervals not
this proposed AD and placed it in the exceeding 10 hours TIS, inspect each Issued in Fort Worth, Texas, on July 15,
AD docket. reinforcement angle for a crack as depicted 2015.
in Figure 1 of Airbus Helicopters Emergency Bruce E. Cain,
List of Subjects in 14 CFR Part 39 Alert Service Bulletin No. 05.00.70 for Model
Acting Directorate Manager, Rotorcraft
AS350B, AS350BA, AS350B1, AS350B2,
mstockstill on DSK4VPTVN1PROD with PROPOSALS
Air transportation, Aircraft, Aviation Directorate, Aircraft Certification Service.
safety, Incorporation by reference, AS350B3, AS350C, AS350D, and AS350D1
helicopters and Airbus Helicopters [FR Doc. 2015–17952 Filed 7–22–15; 8:45 am]
Safety.
Emergency Alert Service Bulletin No. BILLING CODE 4910–13–P
The Proposed Amendment 05.00.62 for AS355E, AS355F, AS355F1,
AS355F2, AS355N, and AS355NP
Accordingly, under the authority helicopters, both Revision 0 and dated March
delegated to me by the Administrator, 24, 2014.
the FAA proposes to amend 14 CFR part (2) If there is a crack, before further flight,
39 as follows: repair the reinforcement angle in a manner
VerDate Sep<11>2014 19:18 Jul 22, 2015 Jkt 235001 PO 00000 Frm 00011 Fmt 4702 Sfmt 9990 E:\FR\FM\23JYP1.SGM 23JYP1](https://thefederalregister.org/doc/80_FR_43786/page/3.svg)
Document Created: 2015-12-15 12:53:40
Document Modified: 2015-12-15 12:53:40
| 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 September 21, 2015. | |
| Contact | Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 80 FR 43645 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR