Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France), 45335-45337 [2014-18247]

Download as PDF Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations 45335 DEPARTMENT OF TRANSPORTATION Examining the AD Docket Discussion Federal Aviation Administration You may examine the AD docket on the Internet at https:// 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 AD, the European Aviation Safety Agency (EASA) AD, any incorporated by reference service information, the economic evaluation, any comments received, and other information. The street address for 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 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 https:// www.airbushelicopters.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email robert.grant@faa.gov. SUPPLEMENTARY INFORMATION: On June 10, 2014, we issued EAD 2014–12–51, which applies to helicopters with 690 or more hours time-in-service (TIS), and requires within 10 hours TIS, dye-penetrant inspecting certain areas of the junction frame for a crack. EAD 2014–12–51 also requires, at intervals not exceeding 25 hours TIS, either repeating the dyepenetrant inspection or performing a borescope inspection of certain areas of the junction frame for a crack. If there is a crack, EAD 2014–12–51 requires replacing the junction frame. EAD 2014–12–51 was sent previously to all known U.S. owners and operators of these helicopters. EAD 2014–12–51 was prompted by EASA EAD No. 2014–0145–E, dated June 6, 2014 (EAD 2014–0145–E). EASA, which is the Technical Agent for the Member States of the European Union, issued EAD 2014–0145–E to correct an unsafe condition for Airbus Helicopters Model EC130B4 and EC130T2 helicopters. EASA advises that following unscheduled inspections, two events of crack propagation through the junction frame of the tailboom/ Fenestron were reported on EC130B4 helicopters, and that an investigation revealed the cracks initiated in the lower right-hand part of the junction frame between the web and the flange where the lower spar of the tailboom is joined. EASA also advises that the cracks were of a significant length, and were not visible from the outside of the helicopter. Finally, EASA advises that this condition, if not detected, could lead to structural failure, possibly resulting in Fenestron detachment and consequent loss of control of the helicopter. EAD 2014–0145–E requires, within 10 hours TIS or 7 days, inspecting the junction frame in the radius between the web and the flange on the tailcone side for a crack. EAD 2014–0145–E also requires, at intervals not exceeding 25 hours TIS, inspecting the frame web for a crack with a borescope. If there is a crack, the EASA AD requires contacting Airbus Helicopters for repair procedures. 14 CFR Part 39 [Docket No. FAA–2014–0515; Directorate Identifier 2014–SW–036–AD; Amendment 39–17921; AD 2014–12–51] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model EC130B4 and EC130T2 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires repetitively inspecting the Fenestron to tailboom junction frame (junction frame) for a crack. This AD is prompted by reports of a crack propagating through the junction frame on two EC130B4 helicopters. These actions are intended to detect a crack and to prevent failure of the junction frame, which could result in loss of the Fenestron and subsequent loss of control of the helicopter. DATES: This AD becomes effective August 20, 2014 to all persons except those persons to whom it was made immediately effective by Emergency AD (EAD) 2014–12–51, issued on June 10, 2014, which contained the requirements of this AD. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of August 20, 2014. We must receive comments on this AD by October 6, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 16:53 Aug 04, 2014 Jkt 232001 Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 FAA’s Determination These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to E:\FR\FM\05AUR1.SGM 05AUR1 45336 Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations exist or develop on other helicopters of these same type designs. Related Service Information Airbus Helicopters has issued Emergency Alert Service Bulletin No. 05A017, Revision 0, dated June 6, 2014 (EASB 05A017) for Model EC130B4 and EC130T2 helicopters. EASB 05A017 describes procedures for inspecting, through the inside of the tailboom, the web of the frame and in the radius between the web and the flange on the tailcone side for a crack. If there is a crack, EASB 05A017 directs operators to contact Airbus Helicopters for specific procedures to return the helicopter to conformity. AD Requirements This AD requires, for helicopters with 690 or more hours TIS: • Within 10 hours TIS, removing the horizontal stabilizer, cleaning the junction frame, and dye-penetrant inspecting the junction frame for a crack in the areas shown in Figure 1 of EASB 05A017; • Within 25 hours of the dyepenetrant inspection, and at intervals not exceeding 25 hours TIS, either repeating the dye-penetrant inspection or, using a borescope, inspecting the junction frame for a crack in the areas shown in Figure 2 of EASB 05A017. • If there is a crack, this AD requires, before further flight, replacing the junction frame. Differences Between This AD and the EASA AD EAD 2014–0145–E allows a visual inspection for the initial 10 hour TIS inspection, while this AD requires a dye-penetrant inspection. If there is a crack, EAD 2014–0145–E requires contacting Airbus Helicopters for approved repair instructions, while this AD requires replacing the junction frame. Finally, EAD 2014–0145–E requires inspecting the junction frame within 10 hours TIS or 7 days, whichever occurs earlier, while this AD requires inspecting within 10 hours TIS. Interim Action mstockstill on DSK4VPTVN1PROD with RULES We consider this EAD to be an interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this AD will affect 194 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. At an average labor rate of $85 per hour, dye-penetrant inspecting the junction frame will require 1 work-hour, VerDate Mar<15>2010 16:53 Aug 04, 2014 Jkt 232001 for a cost per helicopter of $85, and a total cost of $16,490 for the fleet, per inspection cycle. Borescope inspecting the junction frame will require .5 workhour, for a cost per helicopter of $43 and a total cost of $8,342 for the fleet, per inspection cycle. If required, replacing the junction frame will require 50 work-hours, and required parts will cost $60,000, for a cost per helicopter of $64,250. FAA’s Justification and Determination of the Effective Date Providing an opportunity for public comments before adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we found and continue to find that the risk to the flying public justifies waiving notice and comment prior to adopting this rule because the initial required corrective action must be done within 10 hours time-in-service, a very short time period based on the average flight-hour utilization rate of these helicopters. Since it was found that immediate corrective action was required, notice and opportunity for prior public comment before issuing this AD were impracticable and contrary to the public interest and that good cause existed to make the AD effective immediately by EAD 2014–12–51, issued on June 10, 2014, to all known U.S. owners and operators of these helicopters. These conditions still exist and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons. 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. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2014–12–51 Airbus Helicopters (previously Eurocopter France): Amendment 39– 17921; Docket No. FAA–2014–0515; Directorate Identifier 2014–SW–036–AD. (a) Applicability This AD applies to Airbus Helicopters Model EC130B4 and EC130T2 helicopters, with 690 or more hours time-in-service (TIS), certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in the tailboom to Fenestron junction frame (junction frame). This condition could result in failure of the junction frame, which could result in loss of the Fenestron and subsequent loss of control of the helicopter. E:\FR\FM\05AUR1.SGM 05AUR1 Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations (c) Effective Date This AD becomes effective August 20, 2014 to all persons except those persons to whom it was made immediately effective by Emergency AD 2014–12–51, issued on June 10, 2014, which contained the requirements of this AD. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Within 10 hours TIS, remove the horizontal stabilizer, clean the junction frame, and dye-penetrant inspect around the circumference of the junction frame for a crack in the areas shown in Figure 1 of Airbus Helicopters EC130 Emergency Alert Service Bulletin No. 05A017, Revision 0, dated June 6, 2014 (EASB 05A017). Pay particular attention to the area around the 4 spars (item b) of Figure 1 of EASB 05A017. An example of a crack is shown in Figure 3 of EASB 05A017. (2) Within 25 hours TIS of the inspection required by paragraph (e)(1) of this AD, and thereafter at intervals not exceeding 25 hours TIS, either perform the actions of paragraph (e)(1) of this AD or, if the area is clean, using a borescope, inspect around the circumference of the junction frame for a crack in the areas shown in Figure 2 of EASB 05A017. Pay particular attention to the area around the 4 spars (item b) of Figure 2 of EASB 05A017. An example of a crack is shown in Figure 3 of EASB 05A017. (3) If there is a crack, before further flight, replace the junction frame. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Helicopters Emergency Alert Service Bulletin No. 05A017, Revision 0, dated June 6, 2014. (ii) [Reserved] (3) For Airbus Helicopters service information identified in this 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 https://www.air bushelicopters.com/techpub. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may also view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www. archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on July 24, 2014. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–18247 Filed 8–4–14; 8:45 am] BILLING CODE 4910–13–P (f) Special Flight Permits Special flight permits are prohibited. DEPARTMENT OF TRANSPORTATION (g) Alternative Methods of Compliance (AMOCs) Federal Aviation Administration (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, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222– 5110; email robert.grant@faa.gov. (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. mstockstill on DSK4VPTVN1PROD with RULES (h) Additional Information (i) Subject Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft Tailboom. 16:53 Aug 04, 2014 [Docket No. FAA–2014–0056; Directorate Identifier 2013–NM–160–AD; Amendment 39–17906; AD 2014–15–04] RIN 2120–AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was prompted by a report of rudder pedal restriction which was the result of water leakage at the inlet tubing of an in-line heater in the lower part of the forward fuselage. This AD requires deactivating the potable water system, or SUMMARY: The subject of this AD is addressed in European Aviation Safety Agency EAD No. 2014–0145–E, dated June 6, 2014. You may view the EASA AD on the Internet at https:// www.regulations.gov in Docket No. FAA– 2014–0515. VerDate Mar<15>2010 14 CFR Part 39 Jkt 232001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 45337 alternatively filling and activating the potable water system. We are issuing this AD to prevent rudder pedal restriction due to the pitch control mechanism becoming frozen as the result of water spray, which could prevent disconnection and normal pitch control, and consequently result in reduced controllability of the airplane. DATES: This AD becomes effective September 9, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 9, 2014. ADDRESSES: You may examine the AD docket on the Internet at https://www. regulations.gov/#!docketDetail;D=FAA2014-0056; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Saab AB, Saab ¨ Aerosystems, SE–581 88, Linkoping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; email saab2000.tech support@saabgroup.com; Internet https://www.saabgroup.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227– 1112; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. The NPRM published in the Federal Register on February 25, 2014 (79 FR 10433). The NPRM was prompted by a report of rudder pedal restriction which was the result of water leakage at the inlet tubing of an in-line heater in the lower part of the forward fuselage. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0172R1, dated September 6, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the E:\FR\FM\05AUR1.SGM 05AUR1

Agencies

[Federal Register Volume 79, Number 150 (Tuesday, August 5, 2014)]
[Rules and Regulations]
[Pages 45335-45337]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-18247]



[[Page 45335]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0515; Directorate Identifier 2014-SW-036-AD; 
Amendment 39-17921; AD 2014-12-51]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

SUMMARY: We are publishing a new airworthiness directive (AD) for 
Airbus Helicopters Model EC130B4 and EC130T2 helicopters, which was 
sent previously to all known U.S. owners and operators of these 
helicopters. This AD requires repetitively inspecting the Fenestron to 
tailboom junction frame (junction frame) for a crack. This AD is 
prompted by reports of a crack propagating through the junction frame 
on two EC130B4 helicopters. These actions are intended to detect a 
crack and to prevent failure of the junction frame, which could result 
in loss of the Fenestron and subsequent loss of control of the 
helicopter.

DATES: This AD becomes effective August 20, 2014 to all persons except 
those persons to whom it was made immediately effective by Emergency AD 
(EAD) 2014-12-51, issued on June 10, 2014, which contained the 
requirements of this AD.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of August 20, 
2014.
    We must receive comments on this AD by October 6, 2014.

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

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov 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 AD, the European Aviation Safety 
Agency (EASA) AD, any incorporated by reference service information, 
the economic evaluation, any comments received, and other information. 
The street address for 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 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 
https://www.airbushelicopters.com/techpub. You may review the referenced 
service information at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    On June 10, 2014, we issued EAD 2014-12-51, which applies to 
helicopters with 690 or more hours time-in-service (TIS), and requires 
within 10 hours TIS, dye-penetrant inspecting certain areas of the 
junction frame for a crack. EAD 2014-12-51 also requires, at intervals 
not exceeding 25 hours TIS, either repeating the dye-penetrant 
inspection or performing a borescope inspection of certain areas of the 
junction frame for a crack. If there is a crack, EAD 2014-12-51 
requires replacing the junction frame. EAD 2014-12-51 was sent 
previously to all known U.S. owners and operators of these helicopters.
    EAD 2014-12-51 was prompted by EASA EAD No. 2014-0145-E, dated June 
6, 2014 (EAD 2014-0145-E). EASA, which is the Technical Agent for the 
Member States of the European Union, issued EAD 2014-0145-E to correct 
an unsafe condition for Airbus Helicopters Model EC130B4 and EC130T2 
helicopters. EASA advises that following unscheduled inspections, two 
events of crack propagation through the junction frame of the tailboom/
Fenestron were reported on EC130B4 helicopters, and that an 
investigation revealed the cracks initiated in the lower right-hand 
part of the junction frame between the web and the flange where the 
lower spar of the tailboom is joined. EASA also advises that the cracks 
were of a significant length, and were not visible from the outside of 
the helicopter. Finally, EASA advises that this condition, if not 
detected, could lead to structural failure, possibly resulting in 
Fenestron detachment and consequent loss of control of the helicopter. 
EAD 2014-0145-E requires, within 10 hours TIS or 7 days, inspecting the 
junction frame in the radius between the web and the flange on the 
tailcone side for a crack. EAD 2014-0145-E also requires, at intervals 
not exceeding 25 hours TIS, inspecting the frame web for a crack with a 
borescope. If there is a crack, the EASA AD requires contacting Airbus 
Helicopters for repair procedures.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to

[[Page 45336]]

exist or develop on other helicopters of these same type designs.

Related Service Information

    Airbus Helicopters has issued Emergency Alert Service Bulletin No. 
05A017, Revision 0, dated June 6, 2014 (EASB 05A017) for Model EC130B4 
and EC130T2 helicopters. EASB 05A017 describes procedures for 
inspecting, through the inside of the tailboom, the web of the frame 
and in the radius between the web and the flange on the tailcone side 
for a crack. If there is a crack, EASB 05A017 directs operators to 
contact Airbus Helicopters for specific procedures to return the 
helicopter to conformity.

AD Requirements

    This AD requires, for helicopters with 690 or more hours TIS:
     Within 10 hours TIS, removing the horizontal stabilizer, 
cleaning the junction frame, and dye-penetrant inspecting the junction 
frame for a crack in the areas shown in Figure 1 of EASB 05A017;
     Within 25 hours of the dye-penetrant inspection, and at 
intervals not exceeding 25 hours TIS, either repeating the dye-
penetrant inspection or, using a borescope, inspecting the junction 
frame for a crack in the areas shown in Figure 2 of EASB 05A017.
     If there is a crack, this AD requires, before further 
flight, replacing the junction frame.

Differences Between This AD and the EASA AD

    EAD 2014-0145-E allows a visual inspection for the initial 10 hour 
TIS inspection, while this AD requires a dye-penetrant inspection. If 
there is a crack, EAD 2014-0145-E requires contacting Airbus 
Helicopters for approved repair instructions, while this AD requires 
replacing the junction frame. Finally, EAD 2014-0145-E requires 
inspecting the junction frame within 10 hours TIS or 7 days, whichever 
occurs earlier, while this AD requires inspecting within 10 hours TIS.

Interim Action

    We consider this EAD to be an interim action. If final action is 
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this AD will affect 194 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. At an average labor rate of $85 per hour, 
dye-penetrant inspecting the junction frame will require 1 work-hour, 
for a cost per helicopter of $85, and a total cost of $16,490 for the 
fleet, per inspection cycle. Borescope inspecting the junction frame 
will require .5 work-hour, for a cost per helicopter of $43 and a total 
cost of $8,342 for the fleet, per inspection cycle.
    If required, replacing the junction frame will require 50 work-
hours, and required parts will cost $60,000, for a cost per helicopter 
of $64,250.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments before adopting these 
AD requirements would delay implementing the safety actions needed to 
correct this known unsafe condition. Therefore, we found and continue 
to find that the risk to the flying public justifies waiving notice and 
comment prior to adopting this rule because the initial required 
corrective action must be done within 10 hours time-in-service, a very 
short time period based on the average flight-hour utilization rate of 
these helicopters.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment before issuing this AD 
were impracticable and contrary to the public interest and that good 
cause existed to make the AD effective immediately by EAD 2014-12-51, 
issued on June 10, 2014, to all known U.S. owners and operators of 
these helicopters. These conditions still exist and the AD is hereby 
published in the Federal Register as an amendment to section 39.13 of 
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to 
all persons.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

     Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2014-12-51 Airbus Helicopters (previously Eurocopter France): 
Amendment 39-17921; Docket No. FAA-2014-0515; Directorate Identifier 
2014-SW-036-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model EC130B4 and EC130T2 
helicopters, with 690 or more hours time-in-service (TIS), 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the tailboom 
to Fenestron junction frame (junction frame). This condition could 
result in failure of the junction frame, which could result in loss 
of the Fenestron and subsequent loss of control of the helicopter.

[[Page 45337]]

(c) Effective Date

    This AD becomes effective August 20, 2014 to all persons except 
those persons to whom it was made immediately effective by Emergency 
AD 2014-12-51, issued on June 10, 2014, which contained the 
requirements of this AD.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    (1) Within 10 hours TIS, remove the horizontal stabilizer, clean 
the junction frame, and dye-penetrant inspect around the 
circumference of the junction frame for a crack in the areas shown 
in Figure 1 of Airbus Helicopters EC130 Emergency Alert Service 
Bulletin No. 05A017, Revision 0, dated June 6, 2014 (EASB 05A017). 
Pay particular attention to the area around the 4 spars (item b) of 
Figure 1 of EASB 05A017. An example of a crack is shown in Figure 3 
of EASB 05A017.
    (2) Within 25 hours TIS of the inspection required by paragraph 
(e)(1) of this AD, and thereafter at intervals not exceeding 25 
hours TIS, either perform the actions of paragraph (e)(1) of this AD 
or, if the area is clean, using a borescope, inspect around the 
circumference of the junction frame for a crack in the areas shown 
in Figure 2 of EASB 05A017. Pay particular attention to the area 
around the 4 spars (item b) of Figure 2 of EASB 05A017. An example 
of a crack is shown in Figure 3 of EASB 05A017.
    (3) If there is a crack, before further flight, replace the 
junction frame.

(f) Special Flight Permits

    Special flight permits are prohibited.

(g) 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, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone (817) 222-5110; email 
robert.grant@faa.gov.
    (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 EAD No. 2014-0145-E, dated June 6, 2014. You may view the 
EASA AD on the Internet at https://www.regulations.gov in Docket No. 
FAA-2014-0515.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft 
Tailboom.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Helicopters Emergency Alert Service Bulletin No. 
05A017, Revision 0, dated June 6, 2014.
    (ii) [Reserved]
    (3) For Airbus Helicopters service information identified in 
this 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 https://www.airbushelicopters.com/techpub.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may also view this service information that is 
incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on July 24, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-18247 Filed 8-4-14; 8:45 am]
BILLING CODE 4910-13-P
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