80 FR 34335 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) (Airbus Helicopters) Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 115 (June 16, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 115 (June 16, 2015)
| Page Range | 34335-34338 | |
| FR Document | 2015-14282 |
[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)] [Proposed Rules] [Pages 34335-34338] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-14282] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0105; Directorate Identifier 2008-SW-58-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) (Airbus Helicopters) Helicopters AGENCY: Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: This document proposes superseding Airworthiness Directives (AD) 2000-05-17 and AD 2001-04-12, which apply to Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2000-05-17 and AD 2001-04-12 require repetitive visual checks of the engine-to-main gearbox (MGB) coupling tube assembly (coupling tube) for a crack and replacing any cracked tube with an airworthy tube. This proposed AD would require removing certain engine mount parts from service, measuring the height of the engine mounting base for certain helicopters, replacing the engine mount if a certain height is exceeded, inspecting the flared coupling on certain helicopters for a crack, and replacing the coupling if it is cracked. Since we issued AD 2000-05-17 and AD 2001-04-12, there have been reports of additional cracks in coupling tubes. The proposed actions are intended to prevent coupling tube failure, loss of engine drive, and a subsequent forced landing of the helicopter. DATES: We must receive comments on this proposed AD by August 17, 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 Direction Generale de L'Aviation Civile (DGAC) 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, Texas 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub. You may review the 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: James Blyn, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas [[Page 34336]] 76137; telephone (817) 222-5110; email james.blyn@faa.gov. 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 March 6, 2000, we issued AD 2000-05-17, Amendment 39-11627 (65 FR 13875, March 15, 2000) for Model EC120B helicopters with engine coupling tube, part number (P/N) C631A1002101, installed. AD 2000-05-17 requires recurring inspections of each coupling tube for a crack and, if there is a crack, replacing any cracked coupling tube with an airworthy, reinforced coupling tube, P/N C631A1101101, and replacing certain engine support fitting parts. AD 2000-05-17 also requires replacing all affected coupling tubes with a reinforced coupling tube and replacing certain engine support fitting parts by March 31, 2000. AD 2000-05-17 was prompted by reports of cracks on the coupling tubes. On February 20, 2001, we issued AD 2001-04-12, Amendment 39-12131 (66 FR 13232, March 5, 2001), for Model EC120B helicopters with engine coupling tube, P/N C631A1101101, installed. AD 2001-04-12 requires a visual check on each coupling tube for a crack at specified intervals. AD 2001-04-12 was prompted by several reports of cracks on the reinforced coupling tube. AD 2000-05-17 and AD 2001-04-12 were intended to prevent coupling tube failure, loss of engine drive, and a subsequent forced landing. Actions Since AD 2000-05-17 and AD 2001-04-12 Were Issued Since we issued AD 2000-05-17 (65 FR 13875, March 15, 2000) and AD 2001-04-12 (66 FR 13232, March 5, 2001), there have been reports of additional cracks in coupling tubes. Eurocopter France (now Airbus Helicopters) has conducted tests and determined that the washer-type engine mount may, in certain cases, induce excessive loading on the coupling tube since the design does not allow the operators to ensure that all of the parts are correctly assembled. Eurocopter France (now Airbus Helicopters) has also determined that excessive loading results in binding that increases component wear of the inner diameter of the mounting base. The DGAC, on behalf of the European Aviation Safety Agency, issued AD No. F-2003-325 R1, dated May 12, 2004, to correct an unsafe condition for Model EC120B helicopters with engine coupling tube, P/N C631A1101101, and with an engine mount containing certain parts listed in Eurocopter Alert Service Bulletin (ASB) No. 04A005, dated July 16, 2003. DGAC AD No. F-2003-325 R1 requires certain inspections for helicopters with an engine mount block modified in accordance with Eurocopter Service Bulletin (SB) No. 71-003, Revision 1, dated July 18, 2002, replacing any coupling tube that has a crack, and increasing the life limit of the coupling tube from 1,000 flight hours to 20,000 flight hours. Also, DGAC AD No. F-2003-325 R1 requires, for helicopters with a new spring-loaded engine suspension modification in accordance with Eurocopter SB No. 71-005, Revision 0, dated May 14, 2004, increasing the life limit of the coupling tube to 20,000 flight hours and canceling the repetitive inspections of the coupling tube. The DGAC advises that a crack was detected on a reinforced coupling tube, which may lead to coupling tube failure and subsequent autorotation. This action is intended to prevent coupling tube failure, loss of engine drive, and a subsequent forced landing of the helicopter. FAA's Determination This helicopter has been approved by the aviation authority of France and is approved for operation in the United States. Pursuant to our bilateral agreement with France, the DGAC has kept the FAA informed of the situation described above. We are proposing this AD because we evaluated all information provided by the DGAC and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Related Service Information Under 1 CFR Part 51 We reviewed the following Eurocopter service information: ASB No. 04A005, Revision 0, dated July 16, 2003, prohibits, after June 30, 2004, operating an engine mount made up of the following parts: support arm, P/N C714A1107201; swaged support arm, P/N C714A1106201; left-hand support bracket, P/N C714A1101102; and right-hand support bracket, P/N C714A1101103. SB No. 04A005 also specifies measuring the height of the engine mounting base and, if the height is more than 10.5 millimeters, replacing the engine mount with an engine mount that does not have the specified P/N. ASB No. 04A005 does not apply to helicopters modified with an improved engine mount in accordance with SB No. 71-003. ASB No. 04A005 also does not apply to helicopters with a serial number 1170 or larger, as the specified engine mounts are not installed on those helicopters. SB No. 71-005, Revision 0, dated May 14, 2004, contains procedures to modify the spring-type engine suspension system and dye- penetrant inspect the flared coupling assembly. 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. The DGAC classified the service information contained in ASB No. 04A005 and SB No. 71-005 as mandatory and issued AD No. F-2003-325 R1, dated May 12, 2004, to ensure the continued airworthiness of these helicopters. Other Related Service Information We also reviewed the following Eurocopter service information: SB No. 71-003, Revision 1, dated July 18, 2002, contains procedures to improve the engine mount. ASB No. 05A003, Revision 2, dated July 16, 2003, for helicopters that have not been modified with an improved engine mount in accordance with SB No. 71-003, specifies inspecting the coupling tube for a crack every 5 hours and establishing a coupling tube life limit of 1,000 hours. For helicopters that have been modified with an improved engine mount, ASB No. 05A003 [[Page 34337]] specifies inspecting the coupling tube for a crack every 25 hours and increasing the coupling tube life limit to 20,000 hours. ASB No. 05A003 was revised to Revision 3, dated May 11, 2004, to specify an optional spring-type engine suspension modification and cancel the repetitive inspection for this modified configuration. The DGAC also classified the service information contained in SB No. 71-003 and ASB No. 05A003 as mandatory and issued AD No. F-2003-325 R1, dated May 12, 2004, to ensure the continued airworthiness of these helicopters. Proposed AD Requirements This proposed AD would require: Before further flight, for certain helicopters, removing from service certain engine mount parts: support arm, P/N C714A1107201; swaged support arm, P/N C714A1106201; left-hand support bracket, P/N C714A1101102; and right-hand support bracket, P/N C714A1101103. Measuring the height of the engine mounting base and, if the height is more than 10.5 millimeters, replacing the engine mount with an engine mount that does not have the affected parts. Within 25 hours time-in-service (TIS), for certain other helicopters that do not have the specified engine mount parts due to modifications, replacing the spring-type engine suspension system and dye-penetrant inspecting the flared coupling for a crack. If there is a crack in the flared coupling, before further flight, replacing the coupling with an airworthy coupling. Before further flight, removing coupling tube, P/N C631A1002101 from service. This proposed AD would prohibit installing coupling tube, P/N C631A1002101 on any helicopter. Differences Between This Proposed AD and the DGAC AD This proposed AD would require the installation of the spring-type engine suspension modification specified in Eurocopter SB No. 71-005 and would not require the repetitive inspection of the coupling tube and the engine mount base. This proposed AD would not require you to contact the manufacturer. Costs of Compliance We estimate out of 115 helicopters on the U.S. registry about 23 helicopters would be affected by this proposed AD. At an average labor rate of $85 per work hour, we estimate the following: Installing new mounting arms and brackets would require about 12 work hours and required parts would cost $9,194, for a total cost per helicopter of $10,214 and $234,922 for the fleet. Installing the mounting spring kit would require about 14 work hours and required parts would cost $14,621, for a total cost per helicopter of $15,811 and $363,653 for the fleet. Dye-penetrant inspecting the coupling tube would require about 1 work hour for a cost per helicopter of $85 and $1,955 for the 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, 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: 0 a. Removing Airworthiness Directive (AD) 2000-05-17, Amendment 39-11627 (65 FR 13875, March 15, 2000); and AD 2001-04-12, Amendment 39-12131 (66 FR 13232, March 5, 2001); and 0 b. Adding the following new AD: Airbus Helicopters (Previously Eurocopter France): Docket No. FAA- 2014-0105; Directorate Identifier 2008-SW-58-AD. (a) Applicability This AD applies to Model EC120B helicopters with an engine-to- main gearbox coupling tube assembly (coupling tube), part number (P/ N) C631A1101101 or P/N C631A1002101, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a coupling tube. This condition could result in coupling tube failure, loss of engine drive, and a subsequent forced landing of the helicopter. (c) Affected ADs This AD supersedes AD 2000-05-17, Amendment 39-11627 (65 FR 13875, March 15, 2000) and AD 2001-04-12, Amendment 39-12131 (66 FR 13232, March 5, 2001). (d) Comments Due Date We must receive comments by August 17, 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 a serial number up to and including 1169, not modified with an improvement of the engine mount in accordance with Eurocopter Service Bulletin (SB) No. 71-003, Revision 1, dated July 18, 2002 (SB 71-003), or not modified by installing a spring-type engine suspension system in accordance with Eurocopter SB No. 71-005, Revision 0, dated May 14, 2004 (SB 71- 005), before further flight: [[Page 34338]] (i) Remove from service the following engine mount parts: (A) Support arm, P/N C714A1107201; (B) Swaged support arm, P/N C714A1106201; (C) Left-hand support bracket, P/N C714A1101102; and (D) Right-hand support bracket, P/N C714A1101103. (ii) Measure the height of the engine mounting base as depicted in Figure 1 of Eurocopter Alert SB No. 04A005, Revision 0, dated July 16, 2003. If the height is more than 10.5 millimeters, replace the engine mount with an engine mount that does not have the parts identified in paragraph (f)(1)(i) of this AD. (2) For helicopters with a serial number 1170 and larger or helicopters modified with an improvement of the engine mount in accordance with SB 71-003: (i) Within 25 hours TIS, replace the spring-type engine suspension system and perform a dye-penetrant inspection of the flared coupling for a crack by following the Accomplishment Instructions, paragraphs 2.B.2.a through 2.B.2.c of SB 71-005. (ii) If there is a crack in the flared coupling, before further flight, replace the coupling with an airworthy coupling. (3) For helicopters with coupling tube, P/N C631A1002101, installed, before further flight, remove coupling tube, P/N C631A1002101, from service. Do not install coupling tube, P/N C631A1002101, on any helicopter. (g) Special Flight Permits Special flight permits may be issued provided there are no cracks in the coupling tube attachment fitting. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: James Blyn, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222- 5110; email james.blyn@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. (i) Additional Information (1) Eurocopter Alert Service Bulletin (ASB) No. 05A003, Revision 2, dated July 16, 2003, Eurocopter ASB No. 05A003, Revision 3, dated May 11, 2004, and Eurocopter Service Bulletin No. 71-003, Revision 1, dated July 18, 2002, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, Texas 75052, telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in Direction Generale de L'Aviation Civile (DGAC) AD No. F-2003-325 R1, Revision A, dated May 12, 2004. You may view the DGAC AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0105. (j) Subject Joint Aircraft Service Component (JASC) Code: 6310 Engine/ Transmission Coupling--Coupling Tube, Engine Mount, and Engine Mount Base. Issued in Fort Worth, Texas, on May 29, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-14282 Filed 6-15-15; 8:45 am] BILLING CODE 4910-13-P
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servo actuator with servo actuator P/N 222– (i) Additional Information removing certain engine mount parts
382–001–111 or P/N 222–382–001–111FM. (1) Bell Alert Service Bulletin (ASB) No. from service, measuring the height of
(iii) If there is any corrosion that is red or 222–11–111 for Model 222 and 222B the engine mounting base for certain
orange in color, magnetic particle inspect the helicopters, ASB No. 222U–11–82 for Model helicopters, replacing the engine mount
piston rod for a crack. 222U helicopters, ASB No. 230–11–43 for if a certain height is exceeded,
(A) If there is a crack, replace the servo Model 230 helicopters, and ASB No. 430–11– inspecting the flared coupling on certain
actuator with servo actuator, P/N 222–382– 46 for Model 430 helicopters, all Revision A
001–111 or P/N 222–382–001–111FM before
helicopters for a crack, and replacing
and all dated June 22, 2012, which are not
further flight. incorporated by reference, contain additional
the coupling if it is cracked. Since we
(B) If there is no crack, comply with information about the subject of this AD. For issued AD 2000–05–17 and AD 2001–
paragraphs (f)(5) through (f)(7) of this AD. Woodward HRT and Bell service information 04–12, there have been reports of
Within 2,400 hours TIS or 2 years, whichever identified in this AD, contact Bell Helicopter additional cracks in coupling tubes. The
occurs first, replace the servo actuator with Textron Canada Limited, 12,800 Rue de proposed actions are intended to
servo actuator P/N 222–382–001–111 or P/N l’Avenir, Mirabel, Quebec J7J1R4; telephone prevent coupling tube failure, loss of
222–382–001–111FM. (450) 437–2862 or (800) 363–8023; fax (450) engine drive, and a subsequent forced
(iv) If there is no corrosion, visible lack of 433–0272; or at http:// landing of the helicopter.
cadmium plate, or damage to the piston rod, www.bellcustomer.com/files/. You may
review a copy of the service information at DATES: We must receive comments on
comply with paragraphs (f)(5) through and
the FAA, Office of the Regional Counsel, this proposed AD by August 17, 2015.
(f)(7) of this AD. Within 3,000 hours TIS or
4 years, whichever occurs first, replace the Southwest Region, 2601 Meacham Blvd., ADDRESSES: You may send comments by
servo actuator with servo actuator P/N 222– Room 663, Fort Worth, Texas 76137. any of the following methods:
382–001–111 or P/N 222–382–001–111FM. (2) The subject of this AD is addressed in • Federal eRulemaking Docket: Go to
(5) Inspect the portion of the piston rod for the Transport Canada Civil Aviation (TCCA) http://www.regulations.gov. Follow the
any absence of cadmium plating (bare base AD No. CF–2010–29R1, dated July 26, 2012. online instructions for sending your
You may view the TCCA AD on the Internet
metal), as shown in Figure 7 of the
at http://www.regulations.gov in Docket No.
comments electronically.
Woodward ASB. If there is any bare base
FAA–2013–0734. • Fax: 202–493–2251.
metal on the piston rod in this area, apply • Mail: Send comments to the U.S.
brush cadmium plating to all bare and (j) Subject Department of Transportation, Docket
reworked areas using SPS5070 or equivalent Joint Aircraft Service Component (JASC) Operations, M–30, West Building
0.0002 to 0.0005 inch thick and rework the Code: 6730, Rotorcraft Servo System. Ground Floor, Room W12–140, 1200
piston rod by following the Accomplishment
Issued in Fort Worth, Texas, on May 29, New Jersey Avenue SE., Washington,
Instructions, paragraph C., Part III, C.1.1.1.
2015. DC 20590–0001.
through C.1.1.3., of the Woodward ASB.
(6) Reassemble the servo actuator by Lance T. Gant, • Hand Delivery: Deliver to the
following the Accomplishment Instructions, Acting Directorate Manager, Rotorcraft ‘‘Mail’’ address between 9 a.m. and 5
paragraph C, Part III, 1.1.4. through 3.3.4. of Directorate, Aircraft Certification Service. p.m., Monday through Friday, except
the Woodward ASB. [FR Doc. 2015–14278 Filed 6–15–15; 8:45 am] Federal holidays.
(7) Thereafter, overhaul servo actuator P/N BILLING CODE 4910–13–P Examining the AD Docket
222–382–001–111 or P/N 222–382–001–
111FM at intervals not to exceed 10 years or You may examine the AD docket on
10,000 hours TIS, whichever occurs first. DEPARTMENT OF TRANSPORTATION the Internet at http://
www.regulations.gov or in person at the
(g) Credit for Actions Previously Completed
Federal Aviation Administration Docket Operations Office between 9
Compliance with the Woodward ASB or a.m. and 5 p.m., Monday through
with AD 2010–19–51 (75 FR 71540, Friday, except Federal holidays. The AD
November 24, 2010) before the effective date 14 CFR Part 39
docket contains this proposed AD, the
of this AD is considered acceptable for [Docket No. FAA–2014–0105; Directorate
compliance with the corresponding Direction Generale de L’Aviation Civile
Identifier 2008–SW–58–AD]
inspections specified in paragraph (f) of this (DGAC) AD, the economic evaluation,
AD. If you replaced the piston rod pursuant RIN 2120–AA64 any comments received and other
to the Woodward ASB or paragraph (d)(1) or information. The street address for the
(d)(3) of AD 2010–19–51, apply the Airworthiness Directives; Airbus Docket Operations Office (telephone
requirements of paragraph (f)(4)(iv) of this Helicopters (Previously Eurocopter 800–647–5527) is in the ADDRESSES
AD. France) (Airbus Helicopters) section. Comments will be available in
Helicopters the AD docket shortly after receipt.
(h) Alternative Methods of Compliance
(AMOCs) AGENCY: Federal Aviation For service information identified in
Administration, DOT. this proposed AD, contact Airbus
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this Helicopters, Inc., 2701 N. Forum Drive,
ACTION: Notice of proposed rulemaking
AD. Send your proposal to: Matt Wilbanks, Grand Prairie, Texas 75052; telephone
(NPRM).
Aviation Safety Engineer, Regulations and (972) 641–0000 or (800) 232–0323; fax
Policy Group, Rotorcraft Directorate, FAA, SUMMARY: This document proposes (972) 641–3775; or at http://
2601 Meacham Blvd., Fort Worth, Texas superseding Airworthiness Directives www.airbushelicopters.com/techpub.
76137; telephone (817) 222–5110; email (AD) 2000–05–17 and AD 2001–04–12, You may review the service information
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
matt.wilbanks@faa.gov. which apply to Eurocopter France (now at the FAA, Office of the Regional
(2) For operations conducted under a 14 Airbus Helicopters) Model EC120B Counsel, Southwest Region, 2601
CFR part 119 operating certificate or under Meacham Blvd., Room 663, Fort Worth,
helicopters. AD 2000–05–17 and AD
14 CFR part 91, subpart K, we suggest that Texas 76137.
you notify your principal inspector, or
2001–04–12 require repetitive visual
lacking a principal inspector, the manager of checks of the engine-to-main gearbox FOR FURTHER INFORMATION CONTACT:
the local flight standards district office or (MGB) coupling tube assembly James Blyn, Aviation Safety Engineer,
certificate holding district office before (coupling tube) for a crack and replacing Regulations and Policy Group,
operating any aircraft complying with this any cracked tube with an airworthy Rotorcraft Directorate, FAA, 2601
AD through an AMOC. tube. This proposed AD would require Meacham Blvd., Fort Worth, Texas
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specifies inspecting the coupling tube • Installing the mounting spring kit List of Subjects in 14 CFR Part 39
for a crack every 25 hours and would require about 14 work hours and Air transportation, Aircraft, Aviation
increasing the coupling tube life limit to required parts would cost $14,621, for a safety, Incorporation by reference,
20,000 hours. ASB No. 05A003 was total cost per helicopter of $15,811 and Safety.
revised to Revision 3, dated May 11, $363,653 for the fleet.
2004, to specify an optional spring-type The Proposed Amendment
• Dye-penetrant inspecting the
engine suspension modification and coupling tube would require about 1 Accordingly, under the authority
cancel the repetitive inspection for this work hour for a cost per helicopter of delegated to me by the Administrator,
modified configuration. $85 and $1,955 for the fleet. the FAA proposes to amend 14 CFR part
The DGAC also classified the service 39 as follows:
information contained in SB No. 71–003 Authority for This Rulemaking
and ASB No. 05A003 as mandatory and PART 39—AIRWORTHINESS
issued AD No. F–2003–325 R1, dated Title 49 of the United States Code DIRECTIVES
May 12, 2004, to ensure the continued specifies the FAA’s authority to issue
airworthiness of these helicopters. rules on aviation safety. Subtitle I, ■ 1. The authority citation for part 39
section 106, describes the authority of continues to read as follows:
Proposed AD Requirements the FAA Administrator. ‘‘Subtitle VII:
Authority: 49 U.S.C. 106(g), 40113, 44701.
This proposed AD would require: Aviation Programs,’’ describes in more
• Before further flight, for certain detail the scope of the Agency’s § 39.13 [Amended]
helicopters, removing from service authority. ■ 2. The FAA amends § 39.13 by:
certain engine mount parts: support We are issuing this rulemaking under ■ a. Removing Airworthiness Directive
arm, P/N C714A1107201; swaged the authority described in ‘‘Subtitle VII, (AD) 2000–05–17, Amendment 39–
support arm, P/N C714A1106201; left- Part A, Subpart III, Section 44701: 11627 (65 FR 13875, March 15, 2000);
hand support bracket, P/N General requirements.’’ Under that and AD 2001–04–12, Amendment 39–
C714A1101102; and right-hand support section, Congress charges the FAA with 12131 (66 FR 13232, March 5, 2001);
bracket, P/N C714A1101103. Measuring promoting safe flight of civil aircraft in and
the height of the engine mounting base air commerce by prescribing regulations ■ b. Adding the following new AD:
and, if the height is more than 10.5 for practices, methods, and procedures
millimeters, replacing the engine mount Airbus Helicopters (Previously Eurocopter
the Administrator finds necessary for France): Docket No. FAA–2014–0105;
with an engine mount that does not safety in air commerce. This regulation Directorate Identifier 2008–SW–58–AD.
have the affected parts. is within the scope of that authority
• Within 25 hours time-in-service because it addresses an unsafe condition
(a) Applicability
(TIS), for certain other helicopters that that is likely to exist or develop on This AD applies to Model EC120B
do not have the specified engine mount products identified in this rulemaking helicopters with an engine-to-main gearbox
parts due to modifications, replacing the coupling tube assembly (coupling tube), part
action. number (P/N) C631A1101101 or P/N
spring-type engine suspension system
and dye-penetrant inspecting the flared Regulatory Findings C631A1002101, installed, certificated in any
category.
coupling for a crack. If there is a crack
in the flared coupling, before further We determined that this proposed AD (b) Unsafe Condition
flight, replacing the coupling with an would not have federalism implications
This AD defines the unsafe condition as a
airworthy coupling. under Executive Order 13132. This crack in a coupling tube. This condition
• Before further flight, removing proposed AD would not have a could result in coupling tube failure, loss of
coupling tube, P/N C631A1002101 from substantial direct effect on the States, on engine drive, and a subsequent forced
service. This proposed AD would the relationship between the national landing of the helicopter.
prohibit installing coupling tube, P/N Government and the States, or on the
(c) Affected ADs
C631A1002101 on any helicopter. distribution of power and
responsibilities among the various This AD supersedes AD 2000–05–17,
Differences Between This Proposed AD levels of government. Amendment 39–11627 (65 FR 13875, March
and the DGAC AD 15, 2000) and AD 2001–04–12, Amendment
For the reasons discussed, I certify 39–12131 (66 FR 13232, March 5, 2001).
This proposed AD would require the this proposed regulation:
installation of the spring-type engine (d) Comments Due Date
1. Is not a ‘‘significant regulatory We must receive comments by August 17,
suspension modification specified in
action’’ under Executive Order 12866; 2015.
Eurocopter SB No. 71–005 and would
not require the repetitive inspection of 2. Is not a ‘‘significant rule’’ under the (e) Compliance
the coupling tube and the engine mount DOT Regulatory Policies and Procedures
You are responsible for performing each
base. This proposed AD would not (44 FR 11034, February 26, 1979);
action required by this AD within the
require you to contact the manufacturer. 3. Will not affect intrastate aviation in specified compliance time unless it has
Costs of Compliance Alaska to the extent that it justifies already been accomplished prior to that time.
making a regulatory distinction; and (f) Required Actions
We estimate out of 115 helicopters on
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
the U.S. registry about 23 helicopters 4. Will not have a significant (1) For helicopters with a serial number up
would be affected by this proposed AD. economic impact, positive or negative, to and including 1169, not modified with an
At an average labor rate of $85 per work on a substantial number of small entities improvement of the engine mount in
hour, we estimate the following: under the criteria of the Regulatory accordance with Eurocopter Service Bulletin
Flexibility Act. (SB) No. 71–003, Revision 1, dated July 18,
• Installing new mounting arms and 2002 (SB 71–003), or not modified by
brackets would require about 12 work We prepared an economic evaluation installing a spring-type engine suspension
hours and required parts would cost of the estimated costs to comply with system in accordance with Eurocopter SB No.
$9,194, for a total cost per helicopter of this proposed AD and placed it in the 71–005, Revision 0, dated May 14, 2004 (SB
$10,214 and $234,922 for the fleet. AD docket. 71–005), before further flight:
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![34338 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules
(i) Remove from service the following may review a copy of the service information Avenue SE., Washington, DC, between 9
engine mount parts: at the FAA, Office of the Regional Counsel, a.m. and 5 p.m., Monday through
(A) Support arm, P/N C714A1107201; Southwest Region, 2601 Meacham Blvd., Friday, except Federal holidays.
(B) Swaged support arm, P/N Room 663, Fort Worth, Texas 76137.
C714A1106201;
• Fax: Fax comments to Docket
(2) The subject of this AD is addressed in
(C) Left-hand support bracket, P/N Direction Generale de L’Aviation Civile Operations at 202–493–2251.
C714A1101102; and (DGAC) AD No. F–2003–325 R1, Revision A, Privacy: In accordance with 5 U.S.C.
(D) Right-hand support bracket, P/N dated May 12, 2004. You may view the 553(c), DOT solicits comments from the
C714A1101103. DGAC AD on the Internet at http:// public to better inform its rulemaking
(ii) Measure the height of the engine www.regulations.gov in Docket No. FAA– process. DOT posts these comments,
mounting base as depicted in Figure 1 of 2014–0105. without edit, including any personal
Eurocopter Alert SB No. 04A005, Revision 0, information the commenter provides, to
dated July 16, 2003. If the height is more than (j) Subject
10.5 millimeters, replace the engine mount
http://www.regulations.gov, as
Joint Aircraft Service Component (JASC)
with an engine mount that does not have the Code: 6310 Engine/Transmission Coupling—
described in the system of records
parts identified in paragraph (f)(1)(i) of this Coupling Tube, Engine Mount, and Engine notice (DOT/ALL–14 FDMS), which can
AD. Mount Base. be reviewed at http://www.dot.gov/
(2) For helicopters with a serial number privacy.
1170 and larger or helicopters modified with Issued in Fort Worth, Texas, on May 29,
2015.
Docket: Background documents or
an improvement of the engine mount in comments received may be read at
accordance with SB 71–003: Lance T. Gant,
http://www.regulations.gov at any time.
(i) Within 25 hours TIS, replace the spring- Acting Directorate Manager, Rotorcraft
type engine suspension system and perform
Follow the online instructions for
Directorate, Aircraft Certification Service.
a dye-penetrant inspection of the flared accessing the docket or go to the Docket
[FR Doc. 2015–14282 Filed 6–15–15; 8:45 am] Operations in Room W12–140 of the
coupling for a crack by following the
BILLING CODE 4910–13–P West Building Ground Floor at 1200
Accomplishment Instructions, paragraphs
2.B.2.a through 2.B.2.c of SB 71–005. New Jersey Avenue SE., Washington,
(ii) If there is a crack in the flared coupling, DC, between 9 a.m. and 5 p.m., Monday
before further flight, replace the coupling DEPARTMENT OF TRANSPORTATION through Friday, except Federal holidays.
with an airworthy coupling.
(3) For helicopters with coupling tube, P/ Federal Aviation Administration FOR FURTHER INFORMATION CONTACT: For
N C631A1002101, installed, before further technical questions concerning this
flight, remove coupling tube, P/N 14 CFR Parts 61 and 141 action, contact Marcel Bernard, Airmen
C631A1002101, from service. Do not install Certification and Training Branch,
coupling tube, P/N C631A1002101, on any [Docket No.: FAA–2015–1846; Notice No. Flight Standards Service, AFS–810,
helicopter. 15–03]
Federal Aviation Administration, 898
(g) Special Flight Permits RIN 2120–AK71 Airport Park Road, Suite 204, Glen
Special flight permits may be issued Burnie, MD 21061; telephone: (410)
Aviation Training Device Credit for 590–5364 x235 email marcel.bernard@
provided there are no cracks in the coupling
tube attachment fitting.
Pilot Certification faa.gov.
AGENCY: Federal Aviation For legal questions concerning this
(h) Alternative Methods of Compliance
Administration (FAA), DOT. action, contact Anne Moore, Regulations
(AMOCs)
ACTION: Notice of proposed rulemaking.
Division, Office of the Chief Counsel,
(1) The Manager, Safety Management AGC–200, Federal Aviation
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: James Blyn, SUMMARY: This rulemaking proposes to Administration, 800 Independence
Aviation Safety Engineer, Regulations and relieve burdens on pilots seeking to Avenue SW., Washington, DC 20591;
Policy Group, Rotorcraft Directorate, FAA, obtain aeronautical experience, training, telephone (202) 267–3073; email
2601 Meacham Blvd., Fort Worth, Texas and certification by increasing the anne.moore@faa.gov.
76137; telephone (817) 222–5110; email allowed use of aviation training devices. SUPPLEMENTARY INFORMATION:
james.blyn@faa.gov. These actions are necessary to bring the
(2) For operations conducted under a 14 regulations in line with current needs Authority for This Rulemaking
CFR part 119 operating certificate or under and activities of the general aviation The FAA’s authority to issue rules on
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or training community and pilots. aviation safety is found in Title 49 of the
lacking a principal inspector, the manager of DATES: Send comments on or before July United States Code (49 U.S.C.). Subtitle
the local flight standards district office or 16, 2015. I, Section 106 describes the authority of
certificate holding district office before ADDRESSES: Send comments identified the FAA Administrator. Subtitle VII,
operating any aircraft complying with this by docket number FAA–2015–1846 Aviation Programs, describes in more
AD through an AMOC. detail the scope of the agency’s
using any of the following methods:
(i) Additional Information • Federal eRulemaking Portal: Go to authority.
(1) Eurocopter Alert Service Bulletin (ASB) http://www.regulations.gov and follow This rulemaking is promulgated
No. 05A003, Revision 2, dated July 16, 2003, the online instructions for sending your under the authority described in 49
Eurocopter ASB No. 05A003, Revision 3, comments electronically. U.S.C. 106(f), which establishes the
dated May 11, 2004, and Eurocopter Service • Mail: Send comments to Docket authority of the Administrator to
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Bulletin No. 71–003, Revision 1, dated July Operations, M–30; U.S. Department of promulgate regulations and rules; 49
18, 2002, which are not incorporated by Transportation (DOT), 1200 New Jersey U.S.C. 44701(a)(5), which requires the
reference, contain additional information Avenue SE., Room W12–140, West Administrator to promote safe flight of
about the subject of this AD. For service civil aircraft in air commerce by
information identified in this AD, contact
Building Ground Floor, Washington, DC
Airbus Helicopters, Inc., 2701 N. Forum 20590–0001. prescribing regulations and setting
Drive, Grand Prairie, Texas 75052, telephone • Hand Delivery or Courier: Take minimum standards for other practices,
(972) 641–0000 or (800) 232–0323; fax (972) comments to Docket Operations in methods, and procedures necessary for
641–3775; or at http:// Room W12–140 of the West Building safety in air commerce and national
www.airbushelicopters.com/techpub. You Ground Floor at 1200 New Jersey security; and 49 U.S.C. 44703(a), which
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Document Created: 2018-02-22 10:23:11
Document Modified: 2018-02-22 10:23:11
| 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 August 17, 2015. | |
| Contact | James Blyn, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 80 FR 34335 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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