80 FR 52212 - Airworthiness Directives; Continental Motors, Inc. Reciprocating Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 167 (August 28, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 167 (August 28, 2015)
| Page Range | 52212-52215 | |
| FR Document | 2015-21205 |
[Federal Register Volume 80, Number 167 (Friday, August 28, 2015)] [Proposed Rules] [Pages 52212-52215] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-21205] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2012-0002; Directorate Identifier 2011-NE-42-AD] RIN 2120-AA64 Airworthiness Directives; Continental Motors, Inc. Reciprocating Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. ----------------------------------------------------------------------- SUMMARY: We are revising an earlier proposed airworthiness directive (AD) for certain Airmotive Engineering Corp. (AEC) replacement parts manufacturer approval (PMA) cylinder assemblies marketed by Engine Components International Division (ECi). We subsequently issued an initial supplemental NPRM (SNPRM) that proposed to modify the schedule for removal of the affected cylinder assemblies, added that overhauled affected cylinder assemblies be removed within 80 hours, eliminated a reporting requirement, and removed a requirement for initial and repetitive inspections. This second SNPRM reopens the comment period to allow the public the chance to comment on additional information added to the docket of this proposed rule. We are proposing this SNPRM to prevent failure of the cylinder assemblies, which could lead to failure of the engine, in-flight shutdown, and loss of control of the airplane. DATES: We must receive comments on this SNPRM by September 28, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Engine Components International Division, 9503 Middlex Drive, San Antonio, TX 78217; phone: 210-820-8101; Internet: http://www.eci.aero/pages/tech_svcpubs.aspx. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2012- 0002; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jurgen E. Priester, Aerospace Engineer, Delegation Systems Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76137; phone: 817-222- 5190; fax: 817-222-5785; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0002; Directorate Identifier 2011-NE-42-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued an NPRM to amend 14 CFR part 39 by adding an AD that would apply to certain AEC replacement PMA cylinder assemblies marketed by ECi. These assemblies are used on Continental Motors, Inc. (CMI) model 520 and 550 reciprocating engines, and all other CMI engine models approved for the use of models 520 and 550 cylinder assemblies such as the CMI model 470 when modified by STC. The NPRM published in the Federal Register on August 12, 2013 (78 FR 48828). The NPRM proposed to require initial and repetitive inspections, immediate replacement of cracked cylinder assemblies, and replacement of cylinder assemblies at reduced times-in-service (TIS) since new. The NPRM also proposed to prohibit the installation of affected cylinder assemblies into any engine. We subsequently issued an SNPRM which published in the Federal Register on January 8, 2015 (80 FR 1008). The SNPRM proposed a modified schedule for removal of the affected cylinder assemblies, added that overhauled affected cylinder assemblies be removed within 80 hours, eliminated a reporting requirement, and removed the requirement for initial and repetitive inspections. Actions Since Previous SNPRM Was Issued Since we issued the SNPRM (80 FR 1008, January 8, 2015), we received numerous additional comments on the proposed rule. After reviewing the comments, we decided to reopen the docket so that we could provide additional information to explain the rationale for this AD action. We also wanted to provide commenters with the opportunity to comment on this additional information. We added the following information to Docket No. FAA-2012-0002: (1) The risk analysis conducted by the FAA's Chief Scientific and Technical Adviser, Aircraft Safety Analysis; (2) a risk analysis using the Small Airplane Risk Analysis methods; (3) a June 2011, presentation by Airmotive Engineering to the FAA [[Page 52213]] concerning its ECi cylinder assemblies; (4) a list of ECi cylinder assembly failure reports consisting of only those reports where both cylinder serial number and Time in Service are included in the reports; (5) a list of additional failures of ECi cylinder assemblies reported by a maintenance organization; (6) copies of the slides discussed with the NTSB on June 9, 2015 during the meeting with the NTSB to understand its comments to 2011-NE-42-AD, and (7) Airmotive Engineering Corporation Technical Report 1102-13, dated April 30, 2011. In addition, we met with National Transportation Safety Board (NTSB) representatives on June 9, 2015, to clarify the NTSB's basis for its comments of FAA's actions in this proposed rule. We are taking this opportunity to respond to a limited number of comments. Specifically, we found that numerous commenters cited differences between the FAA's proposed action and the NTSB's recommendations in NTSB Safety Recommendation A-12-7. We will respond to remaining comments to the initial SNPRM (80 FR 1008, January 8, 2015) and to this second SNPRM when we issue the final rule. Comments to the Previous SNPRM Request To Provide Supporting Information Danbury Aerospace, Inc., and others in their comments to the SNPRM (80 FR 1008, January 8, 2015), requested that we provide additional information that supports this AD action. We agree. We added our risk analyses and other technical information, such as the list of cylinder failures noted above and ECi Technical Report 1102-13 that supports this proposed rule, to Docket No. FAA-2012-0002 to help commenters and the general public understand the need for this proposed rule. Request To Withdraw the SNPRM Because ECi Cylinder Assemblies Are Not Unsafe Several operators, maintenance organizations, and private citizens asked that we withdraw the SNPRM (80 FR 1008, January 8, 2015) because the affected ECi cylinder assemblies have an equivalent, or lower, failure rate than that of cylinder assemblies manufactured by the original equipment manufacturer (OEM). We disagree. We found that the failure rate for ECi cylinder assemblies is much higher than for OEM cylinder assemblies over the same period. Accident data confirms, that engines and airplanes may not always continue to operate safely with a separated cylinder and that separated cylinders have been the precipitating event in at least two fatal accidents. This accident data is included in the risk analyses that we uploaded to the docket (see NTSB Accident Identifiers NYC02FA178 and ERA11WA008, which are cited in these analyses). We did not withdraw this proposed rule. Request To Review Comparison of Failure Rate Between OEM and ECi Cylinder Assemblies The NTSB commented that the comparison between failure rates of OEM and ECi cylinder assemblies was not valid because the cylinder heads represented substantially different designs. We disagree that the comparison between OEM and ECi cylinder assemblies is not valid. The ECi PMA design was reverse engineered by ECi from earlier vintage OEM cylinders, and uses the same time between overhaul (TBO) as the OEM cylinders. Since these ECi cylinder assemblies are approved to the same TBO as the OEM cylinders, the ECi cylinders should have durability that is equivalent to the OEM cylinders. Our comparison of ECi cylinder assembly service history with the OEM cylinder assembly history showed that the rate of separation for the affected ECi cylinder assemblies is at least 32 times greater than that of OEM cylinder assemblies over the same period. We uploaded this data for commenter review. It may be viewed in Docket No. FAA- 2012-0002. We did not change this proposed AD. Request To Revise Applicability The NTSB commented that it has not investigated any cases involving engines with cylinder assemblies ranging from serial number (S/N) 1 through S/N 1043. The NTSB indicated that cylinder assemblies in this S/N range should not be affected by the AD. We disagree. Cylinder assemblies with S/N 1 through S/N 1043 have the same design as noted in this SNPRM, exhibit the same unsafe condition, and therefore must be included in the applicability. We did not change this proposed AD. The NTSB also commented that AD 2004-08-10, which was issued on May 5, 2004, requires replacement before further flight of ECi cylinder assemblies ranging from S/N 1044 through S/N 7708 installed on CMI 520 and 550 series engines. According to AD 2004-08-10, ECi identified a manufacturing discrepancy that occurred between September 2002 and May 2003 affecting cylinder assemblies S/N 1044 through S/N 7708, which resulted in an over-hardened condition that would reduce the fatigue strength of the aluminum cylinder head. The NTSB commented, therefore, that cylinder assemblies S/N 1044 through S/N 7708 should not be included in the proposed AD. We disagree. AD 2004-08-10 does not apply to all cylinder assemblies S/N 1044 through S/N 7708; it applies only to cylinder assemblies having specific cast markings. Cylinder assemblies S/N 1004 through S/N 7708 have the same design as noted in this SNPRM, exhibit the same unsafe condition, and therefore must be included in the applicability. We did not change this proposed AD. The NTSB also commented that, based on its review of the additional seal band interference fit data provided by ECi, action is only required for 165 cylinder assemblies S/N 36210 through S/N 61176. We disagree. We have received reports of separations of cylinder assemblies S/N 36210 through S/N 61176 that were not among the 165 cylinders that ECi claimed may be at risk for separation due to insufficient head to barrel interference fit. We have uploaded information in Docket No. FAA-2012-0002 that identifies S/Ns of failed cylinder assemblies that were not among the 165 cylinder assemblies identified by ECi. We did not change this proposed AD. The NTSB commented that the applicability represented by the SNPRM--S/N 1 through S/N 61176--represents a much larger number of affected cylinder assemblies than is supported by its investigations. We disagree. ECi's next increase in the design interference fit was incorporated beginning with S/N 61177. Consequently, all cylinder assemblies S/N 1 through S/N 61176 are at risk for separation in the first thread due to insufficient interference fit. We, therefore, find that based on service failure data, identified in the docket as ``U.S. DOT/FAA--04 ECi 520-550 Cylinder Separations,'' and ECI's implementation of design improvements, this proposed AD must apply to cylinder assemblies S/N 1 through S/N 61176. We did not change this proposed AD. Request To Include Repetitive Inspection Requirement The NTSB commented that we should impose a repetitive inspection requirement for certain ECi cylinder assemblies and their removal once they reach the manufacturer's recommended TBO. This repetitive inspection requirement was part of the NPRM (78 [[Page 52214]] FR 48828, August 12, 2013), but we removed it from the SNPRM (80 FR 1008, January 8, 2015). The NTSB observed that the FAA had published Special Airworthiness Information Bulletin (SAIB) NE-07-09R1, dated March 21, 2007, and approved ECi Mandatory Service Bulletin 06-2, Revision 2, dated October 26, 2006. Both of these documents emphasize the importance of conducting periodic inspections of ECi cylinder assemblies. We disagree. We have found, based on service experience since the publication of SAIB NE-07-09R1, that the inspection and tests are not reliable in detecting cracked cylinders and the cost associated with such ongoing tests outweighs the safety benefit. In addition, the crack propagation growth rate is unknown. As a result, we have received field reports of separated cylinders that occurred within the repetitive 50- hour compression test and leak check inspection intervals proposed by the NPRM. We did not change this proposed AD. The NTSB also noted that repetitive inspections are not perfect but are still effective in detecting cracks that have propagated through the cylinder wall. These inspections provide an added level of safety from the time of the issuance of the final rule AD until the required removal of the cylinder assembly. We disagree. We find that repetitive inspections until TBO are inconsistent with the serious hazard represented by cylinder assembly failures. See the ``U.S. DOT/FAA-01 Risk Analysis White Paper'' for 2011-NE-42-AD that we uploaded to the AD docket on June 23, 2015. Therefore, we are requiring removal of affected cylinder assemblies from service prior to TBO. We did not change this proposed AD. FAA's Determination We are proposing this SNPRM to allow the public the opportunity to comment on additional information we added to the docket of this proposed rule. Proposed Requirements of this SNPRM As proposed in the first SNPRM published on January 8, 2015 (80 FR 1008), this second SNPRM would require removal of the affected cylinder assemblies, including overhauled cylinder assemblies, according to a phased removal schedule. Costs of Compliance We estimate that this proposed AD would affect about 5,000 CMI models IO-520, TSIO-520, IO-550, and IOF-550 reciprocating engines and all other CMI engine models approved for the use of CMI models 520 and 550 cylinder assemblies (such as the CMI model 470 when modified by STC), installed on airplanes of U.S. registry. The average labor rate is $85 per hour. We estimate that about 18 hours would be required to replace all six cylinder assemblies during overhaul maintenance. We estimate the pro-rated value of the cost of replacement of six cylinder assemblies to be about $4,202 per engine. Based on these figures, we estimate the total cost of this proposed AD to U.S. operators to change all ECi cylinder assemblies to be $28,660,000. Our cost estimate is exclusive of possible warranty coverage. 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 above, 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. 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 adding the following new airworthiness directive (AD): Continental Motors, Inc. (formerly Teledyne Continental Motors, Inc., formerly Continental): Docket No. FAA-2012-0002; Directorate Identifier 2011-NE-42-AD. (a) Comments Due Date We must receive comments by September 28, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all Continental Motors, Inc. (CMI) model 520 and 550 reciprocating engines, and to all other CMI engine models approved for the use of model 520 and 550 cylinder assemblies such as the CMI model 470 when modified by supplemental type certificate (STC), with Airmotive Engineering Corp. replacement parts manufacturer approval (PMA) cylinder assemblies, marketed by Engine Components International Division (hereinafter referred to as ECi), part number (P/N) AEC631397, with ECi Class 71 or Class 76, serial number (S/N) 1 through S/N 61176, installed. (d) Unsafe Condition This AD was prompted by multiple failure reports of cylinder head-to-barrel separations and cracked and leaking aluminum cylinder heads. We are issuing this AD to prevent failure of the cylinder assemblies, which could lead to failure of the engine, in-flight shutdown, and loss of control of the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Review the engine maintenance records to determine if any affected cylinder assemblies are installed. (2) If you cannot determine based on review of engine maintenance records if any affected cylinder assemblies are installed, comply with paragraph (e)(4) of this AD. [[Page 52215]] (3) If you do not have any of the affected ECi cylinder assemblies installed on your engine, no further action is required. (4) Cylinder Identification and Serial Number Location (i) Check the cylinder assembly P/N and Class number. The ECi cylinder assembly, P/N AEC631397, Class 71 or Class 76, is stamped on the bottom flange of the cylinder barrel. Guidance on the P/N and Class number description and location can be found in ECi Service Instruction No. 99-8-1, Revision 9, dated February 23, 2009. (ii) If you cannot see the cylinder assembly P/N when the cylinder assembly is installed on the engine, you may use the following alternative method of identification: (A) Remove the cylinder assembly rocker box cover. (B) Find the letters ECi, cast into the cylinder head between the valve stems. (C) Check the cylinder head casting P/N. Affected cylinder assemblies have the cylinder head casting P/N, AEC65385, cast into the cylinder head between the valve stems. (D) Find the cylinder assembly S/N as specified in paragraph (e)(4)(iii) or (e)(4)(iv) of this AD, as applicable. (iii) For ECi cylinder assemblies, P/N AEC631397, manufactured through 2008, find the cylinder assembly S/N stamped on the intake port boss two inches down from the top edge of the head. (iv) For ECi cylinder assemblies, P/N AEC631397, manufactured on or after January 1, 2009, find the cylinder assembly S/N stamped just below the top edge of the head on the exhaust port side. (5) Removal From Service (i) For any affected cylinder assembly with 680 or fewer operating hours time-in-service (TIS) since new on the effective date of this AD, remove the cylinder assembly from service before reaching 1,000 operating hours TIS since new. (ii) For any affected cylinder assembly with more than 680 operating hours TIS since new and 1,000 or fewer operating hours TIS since new on the effective date of this AD, remove the cylinder assembly from service within the next 320 operating hours TIS or within 1,160 operating hours TIS since new, whichever occurs first. (iii) For any affected cylinder assembly with more than 1,000 operating hours TIS since new on the effective date of this AD, remove the cylinder assembly from service within the next 160 operating hours or at next engine overhaul, whichever occurs first. (iv) For any affected cylinder assembly that has been overhauled, remove the cylinder assembly from service within the next 80 operating hours TIS after the effective date of this AD. (f) Installation Prohibitions After the effective date of this AD: (1) Do not repair, or reinstall onto any engine, any cylinder assembly removed per this AD. (2) Do not install any affected ECi cylinder assembly that has been overhauled, into any engine. (3) Do not install any engine that has one or more affected overhauled ECi cylinder assemblies, onto any aircraft. (4) Do not return to service any aircraft that has an engine installed with an ECi cylinder assembly subject to this AD, if the cylinder assembly has 1,000 or more operating hours TIS. (g) Alternative Methods of Compliance (AMOCs) The Manager, Delegation Systems Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (h) Related Information (1) For more information about this AD, contact Jurgen E. Priester, Aerospace Engineer, Delegation Systems Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76193; phone: 817-222-5190; fax: 817-222-5785; email: [email protected]. (2) For ECi Service Instruction No. 99-8-1, Revision 9, dated February 23, 2009, contact Engine Components International Division, 9503 Middlex Drive, San Antonio, TX 78217; phone: 210-820-8101; Internet: http://www.eci.aero/pages/tech_svcpubs.aspx. (3) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. Issued in Burlington, Massachusetts, on August 10, 2015. Colleen M. D'Alessandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015-21205 Filed 8-27-15; 8:45 am] BILLING CODE 4910-13-P
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List of Subjects in 14 CFR Part 39 11.43 and 11.45, by any of the following aspects of this proposed AD. We will
Air transportation, Aircraft, Aviation methods: consider all comments received by the
safety, Incorporation by reference, • Federal eRulemaking Portal: Go to closing date and may amend this
Safety. http://www.regulations.gov. Follow the proposed AD because of those
instructions for submitting comments. comments.
The Withdrawal • Fax: 202–493–2251. We will post all comments we
Accordingly, we withdraw the NPRM, • Mail: U.S. Department of receive, without change, to http://
Docket No. FAA–2013–0627, Directorate Transportation, Docket Operations, M– www.regulations.gov, including any
Identifier 2012–NM–021–AD, which 30, West Building Ground Floor, Room personal information you provide. We
was published in the Federal Register W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
on July 24, 2013 (78 FR 44469). Washington, DC 20590. substantive verbal contact we receive
Issued in Renton, Washington, on August
• Hand Delivery: U.S. Department of about this proposed AD.
20, 2015. Transportation, Docket Operations, M– Discussion
Kevin Hull, 30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE., We issued an NPRM to amend 14 CFR
Acting Manager, Transport Airplane part 39 by adding an AD that would
Directorate, Aircraft Certification Service. Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday, apply to certain AEC replacement PMA
[FR Doc. 2015–21247 Filed 8–27–15; 8:45 am] cylinder assemblies marketed by ECi.
except Federal holidays.
BILLING CODE 4910–13–P
For service information identified in These assemblies are used on
this proposed AD, contact Engine Continental Motors, Inc. (CMI) model
Components International Division, 520 and 550 reciprocating engines, and
DEPARTMENT OF TRANSPORTATION all other CMI engine models approved
9503 Middlex Drive, San Antonio, TX
for the use of models 520 and 550
Federal Aviation Administration 78217; phone: 210–820–8101; Internet:
cylinder assemblies such as the CMI
http://www.eci.aero/pages/tech_
model 470 when modified by STC. The
14 CFR Part 39 svcpubs.aspx. You may view this
NPRM published in the Federal
service information at the FAA, Engine
[Docket No. FAA–2012–0002; Directorate Register on August 12, 2013 (78 FR
& Propeller Directorate, 12 New England
Identifier 2011–NE–42–AD] 48828). The NPRM proposed to require
Executive Park, Burlington, MA. For
RIN 2120–AA64
initial and repetitive inspections,
information on the availability of this
immediate replacement of cracked
material at the FAA, call 781–238–7125.
Airworthiness Directives; Continental cylinder assemblies, and replacement of
Motors, Inc. Reciprocating Engines Examining the AD Docket cylinder assemblies at reduced times-in-
You may examine the AD docket on service (TIS) since new. The NPRM also
AGENCY: Federal Aviation proposed to prohibit the installation of
Administration (FAA), DOT. the Internet at http://
www.regulations.gov by searching for affected cylinder assemblies into any
ACTION: Supplemental notice of engine.
proposed rulemaking (NPRM); and locating Docket No. FAA–2012–
We subsequently issued an SNPRM
reopening of comment period. 0002; or in person at the Docket
which published in the Federal Register
Management Facility between 9 a.m.
on January 8, 2015 (80 FR 1008). The
SUMMARY: We are revising an earlier and 5 p.m., Monday through Friday,
SNPRM proposed a modified schedule
proposed airworthiness directive (AD) except Federal holidays. The AD docket
for removal of the affected cylinder
for certain Airmotive Engineering Corp. contains this proposed AD, the
assemblies, added that overhauled
(AEC) replacement parts manufacturer regulatory evaluation, any comments
affected cylinder assemblies be removed
approval (PMA) cylinder assemblies received, and other information. The
within 80 hours, eliminated a reporting
marketed by Engine Components street address for the Docket Office
requirement, and removed the
International Division (ECi). We (phone: 800–647–5527) is in the
requirement for initial and repetitive
subsequently issued an initial ADDRESSES section. Comments will be
inspections.
supplemental NPRM (SNPRM) that available in the AD docket shortly after
proposed to modify the schedule for receipt. Actions Since Previous SNPRM Was
removal of the affected cylinder FOR FURTHER INFORMATION CONTACT: Issued
assemblies, added that overhauled Jurgen E. Priester, Aerospace Engineer, Since we issued the SNPRM (80 FR
affected cylinder assemblies be removed Delegation Systems Certification Office, 1008, January 8, 2015), we received
within 80 hours, eliminated a reporting FAA, Rotorcraft Directorate, 2601 numerous additional comments on the
requirement, and removed a Meacham Blvd., Fort Worth, TX 76137; proposed rule. After reviewing the
requirement for initial and repetitive phone: 817–222–5190; fax: 817–222– comments, we decided to reopen the
inspections. This second SNPRM 5785; email: jurgen.e.priester@faa.gov. docket so that we could provide
reopens the comment period to allow SUPPLEMENTARY INFORMATION: additional information to explain the
the public the chance to comment on rationale for this AD action. We also
additional information added to the Comments Invited wanted to provide commenters with the
docket of this proposed rule. We are We invite you to send any written opportunity to comment on this
proposing this SNPRM to prevent relevant data, views, or arguments about additional information. We added the
failure of the cylinder assemblies, which
Lhorne on DSK5TPTVN1PROD with PROPOSALS
this proposed AD. Send your comments following information to Docket No.
could lead to failure of the engine, in- to an address listed under the FAA–2012–0002: (1) The risk analysis
flight shutdown, and loss of control of ADDRESSES section. Include ‘‘Docket No. conducted by the FAA’s Chief Scientific
the airplane. FAA–2012–0002; Directorate Identifier and Technical Adviser, Aircraft Safety
DATES: We must receive comments on 2011–NE–42–AD’’ at the beginning of Analysis; (2) a risk analysis using the
this SNPRM by September 28, 2015. your comments. We specifically invite Small Airplane Risk Analysis methods;
ADDRESSES: You may send comments, comments on the overall regulatory, (3) a June 2011, presentation by
using the procedures found in 14 CFR economic, environmental, and energy Airmotive Engineering to the FAA
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![52214 Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules
FR 48828, August 12, 2013), but we 550 reciprocating engines and all other on a substantial number of small entities
removed it from the SNPRM (80 FR CMI engine models approved for the use under the criteria of the Regulatory
1008, January 8, 2015). of CMI models 520 and 550 cylinder Flexibility Act.
The NTSB observed that the FAA had assemblies (such as the CMI model 470
List of Subjects in 14 CFR Part 39
published Special Airworthiness when modified by STC), installed on
Information Bulletin (SAIB) NE–07– airplanes of U.S. registry. The average Air transportation, Aircraft, Aviation
09R1, dated March 21, 2007, and labor rate is $85 per hour. We estimate safety, Incorporation by reference,
approved ECi Mandatory Service that about 18 hours would be required Safety.
Bulletin 06–2, Revision 2, dated October to replace all six cylinder assemblies The Proposed Amendment
26, 2006. Both of these documents during overhaul maintenance. We
emphasize the importance of estimate the pro-rated value of the cost Accordingly, under the authority
conducting periodic inspections of ECi of replacement of six cylinder delegated to me by the Administrator,
cylinder assemblies. assemblies to be about $4,202 per the FAA proposes to amend 14 CFR part
We disagree. We have found, based on engine. Based on these figures, we 39 as follows:
service experience since the publication estimate the total cost of this proposed PART 39—AIRWORTHINESS
of SAIB NE–07–09R1, that the AD to U.S. operators to change all ECi DIRECTIVES
inspection and tests are not reliable in cylinder assemblies to be $28,660,000.
detecting cracked cylinders and the cost Our cost estimate is exclusive of ■ 1. The authority citation for part 39
associated with such ongoing tests possible warranty coverage. continues to read as follows:
outweighs the safety benefit. In
Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701.
addition, the crack propagation growth
rate is unknown. As a result, we have Title 49 of the United States Code § 39.13 [Amended]
received field reports of separated specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by adding
cylinders that occurred within the rules on aviation safety. Subtitle I, the following new airworthiness
repetitive 50-hour compression test and section 106, describes the authority of directive (AD):
leak check inspection intervals the FAA Administrator. ‘‘Subtitle VII:
Continental Motors, Inc. (formerly Teledyne
proposed by the NPRM. We did not Aviation Programs’’ describes in more Continental Motors, Inc., formerly
change this proposed AD. detail the scope of the Agency’s Continental): Docket No. FAA–2012–
The NTSB also noted that repetitive authority. 0002; Directorate Identifier 2011–NE–
inspections are not perfect but are still We are issuing this rulemaking under 42–AD.
effective in detecting cracks that have the authority described in Subtitle VII,
(a) Comments Due Date
propagated through the cylinder wall. Part A, Subpart III, Section 44701:
These inspections provide an added ‘‘General requirements.’’ Under that We must receive comments by September
28, 2015.
level of safety from the time of the section, Congress charges the FAA with
issuance of the final rule AD until the promoting safe flight of civil aircraft in (b) Affected ADs
required removal of the cylinder air commerce by prescribing regulations None.
assembly. for practices, methods, and procedures
(c) Applicability
We disagree. We find that repetitive the Administrator finds necessary for
inspections until TBO are inconsistent safety in air commerce. This regulation This AD applies to all Continental Motors,
with the serious hazard represented by Inc. (CMI) model 520 and 550 reciprocating
is within the scope of that authority
engines, and to all other CMI engine models
cylinder assembly failures. See the because it addresses an unsafe condition approved for the use of model 520 and 550
‘‘U.S. DOT/FAA–01 Risk Analysis that is likely to exist or develop on cylinder assemblies such as the CMI model
White Paper’’ for 2011–NE–42–AD that products identified in this rulemaking 470 when modified by supplemental type
we uploaded to the AD docket on June action. certificate (STC), with Airmotive Engineering
23, 2015. Therefore, we are requiring Corp. replacement parts manufacturer
Regulatory Findings approval (PMA) cylinder assemblies,
removal of affected cylinder assemblies
from service prior to TBO. We did not We determined that this proposed AD marketed by Engine Components
would not have federalism implications International Division (hereinafter referred to
change this proposed AD. as ECi), part number (P/N) AEC631397, with
under Executive Order 13132. This ECi Class 71 or Class 76, serial number (S/
FAA’s Determination proposed AD would not have a N) 1 through S/N 61176, installed.
We are proposing this SNPRM to substantial direct effect on the States, on
allow the public the opportunity to the relationship between the national (d) Unsafe Condition
comment on additional information we Government and the States, or on the This AD was prompted by multiple failure
added to the docket of this proposed distribution of power and reports of cylinder head-to-barrel separations
rule. responsibilities among the various and cracked and leaking aluminum cylinder
heads. We are issuing this AD to prevent
levels of government.
Proposed Requirements of this SNPRM For the reasons discussed above, I
failure of the cylinder assemblies, which
could lead to failure of the engine, in-flight
As proposed in the first SNPRM certify this proposed regulation: shutdown, and loss of control of the airplane.
published on January 8, 2015 (80 FR (1) Is not a ‘‘significant regulatory
1008), this second SNPRM would action’’ under Executive Order 12866, (e) Compliance
require removal of the affected cylinder (2) Is not a ‘‘significant rule’’ under Comply with this AD within the
Lhorne on DSK5TPTVN1PROD with PROPOSALS
assemblies, including overhauled the DOT Regulatory Policies and compliance times specified, unless already
cylinder assemblies, according to a Procedures (44 FR 11034, February 26, done.
(1) Review the engine maintenance records
phased removal schedule. 1979),
to determine if any affected cylinder
(3) Will not affect intrastate aviation assemblies are installed.
Costs of Compliance in Alaska to the extent that it justifies (2) If you cannot determine based on
We estimate that this proposed AD making a regulatory distinction, and review of engine maintenance records if any
would affect about 5,000 CMI models (4) Will not have a significant affected cylinder assemblies are installed,
IO–520, TSIO–520, IO–550, and IOF– economic impact, positive or negative, comply with paragraph (e)(4) of this AD.
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![Federal Register / Vol. 80, No. 167 / Friday, August 28, 2015 / Proposed Rules 52215
(3) If you do not have any of the affected (3) Do not install any engine that has one aviation product. The MCAI describes
ECi cylinder assemblies installed on your or more affected overhauled ECi cylinder the unsafe condition as corrosion of the
engine, no further action is required. assemblies, onto any aircraft. horizontal stabilizer. We are issuing this
(4) Do not return to service any aircraft that
(4) Cylinder Identification and Serial Number proposed AD to require actions to
has an engine installed with an ECi cylinder
Location assembly subject to this AD, if the cylinder address the unsafe condition on these
(i) Check the cylinder assembly P/N and assembly has 1,000 or more operating hours products.
Class number. The ECi cylinder assembly, P/ TIS. DATES: We must receive comments on
N AEC631397, Class 71 or Class 76, is this proposed AD by October 13, 2015.
stamped on the bottom flange of the cylinder (g) Alternative Methods of Compliance
(AMOCs) ADDRESSES: You may send comments by
barrel. Guidance on the P/N and Class
number description and location can be The Manager, Delegation Systems any of the following methods:
found in ECi Service Instruction No. 99–8– Certification Office, may approve AMOCs for • Federal eRulemaking Portal: Go to
1, Revision 9, dated February 23, 2009. this AD. Use the procedures found in 14 CFR http://www.regulations.gov. Follow the
(ii) If you cannot see the cylinder assembly 39.19 to make your request. instructions for submitting comments.
P/N when the cylinder assembly is installed • Fax: (202) 493–2251.
(h) Related Information
on the engine, you may use the following • Mail: U.S. Department of
alternative method of identification: (1) For more information about this AD, Transportation, Docket Operations, M–
(A) Remove the cylinder assembly rocker contact Jurgen E. Priester, Aerospace 30, West Building Ground Floor, Room
box cover. Engineer, Delegation Systems Certification
Office, FAA, Rotorcraft Directorate, 2601
W12–140, 1200 New Jersey Avenue SE.,
(B) Find the letters ECi, cast into the Washington, DC 20590.
cylinder head between the valve stems. Meacham Blvd., Fort Worth, TX 76193;
phone: 817–222–5190; fax: 817–222–5785; • Hand Delivery: U.S. Department of
(C) Check the cylinder head casting P/N.
Affected cylinder assemblies have the email: jurgen.e.priester@faa.gov. Transportation, Docket Operations, M–
cylinder head casting P/N, AEC65385, cast (2) For ECi Service Instruction No. 99–8– 30, West Building Ground Floor, Room
into the cylinder head between the valve 1, Revision 9, dated February 23, 2009, W12–140, 1200 New Jersey Avenue SE.,
stems. contact Engine Components International Washington, DC 20590, between 9 a.m.
(D) Find the cylinder assembly S/N as Division, 9503 Middlex Drive, San Antonio, and 5 p.m., Monday through Friday,
specified in paragraph (e)(4)(iii) or (e)(4)(iv) TX 78217; phone: 210–820–8101; Internet: except Federal holidays.
of this AD, as applicable. http://www.eci.aero/pages/tech_ For service information identified in
(iii) For ECi cylinder assemblies, P/N svcpubs.aspx.
this proposed AD, contact SOCATA,
AEC631397, manufactured through 2008, (3) You may view this service information
at the FAA, Engine & Propeller Directorate, Direction des Services, 65921 Tarbes
find the cylinder assembly S/N stamped on
12 New England Executive Park, Burlington, Cedex 9, France; telephone: 33 (0)5
the intake port boss two inches down from
the top edge of the head. MA. For information on the availability of 62.41.73.00; fax: 33 (0)5 62.41.76.54; or
(iv) For ECi cylinder assemblies, P/N this material at the FAA, call 781–238–7125. SOCATA North America, North Perry
AEC631397, manufactured on or after Issued in Burlington, Massachusetts, on Airport, 7501 S Airport Rd., Pembroke
January 1, 2009, find the cylinder assembly August 10, 2015. Pines, Florida 33023, telephone: (954)
S/N stamped just below the top edge of the
Colleen M. D’Alessandro, 893–1400; fax: (954) 964–4141; Internet:
head on the exhaust port side. http://www.socata.com. You may
Directorate Manager, Engine & Propeller
(5) Removal From Service Directorate, Aircraft Certification Service. review this referenced service
information at the FAA, Small Airplane
(i) For any affected cylinder assembly with [FR Doc. 2015–21205 Filed 8–27–15; 8:45 am]
680 or fewer operating hours time-in-service Directorate, 901 Locust, Kansas City,
BILLING CODE 4910–13–P
(TIS) since new on the effective date of this Missouri 64106. For information on the
AD, remove the cylinder assembly from availability of this material at the FAA,
service before reaching 1,000 operating hours DEPARTMENT OF TRANSPORTATION call (816) 329–4148.
TIS since new.
(ii) For any affected cylinder assembly with Examining the AD Docket
Federal Aviation Administration
more than 680 operating hours TIS since new You may examine the AD docket on
and 1,000 or fewer operating hours TIS since the Internet at http://
new on the effective date of this AD, remove 14 CFR Part 39
www.regulations.gov by searching for
the cylinder assembly from service within [Docket No. FAA–2015–3642; Directorate and locating Docket No. FAA–2015–
the next 320 operating hours TIS or within Identifier 2015–CE–028–AD] 3642; or in person at the Docket
1,160 operating hours TIS since new,
whichever occurs first. RIN 2120–AA64 Management Facility between 9 a.m.
(iii) For any affected cylinder assembly and 5 p.m., Monday through Friday,
with more than 1,000 operating hours TIS Airworthiness Directives; SOCATA except Federal holidays. The AD docket
since new on the effective date of this AD, Airplanes contains this proposed AD, the
remove the cylinder assembly from service regulatory evaluation, any comments
within the next 160 operating hours or at AGENCY: Federal Aviation
received, and other information. The
next engine overhaul, whichever occurs first. Administration (FAA), Department of
street address for the Docket Office
(iv) For any affected cylinder assembly that Transportation (DOT).
(telephone (800) 647–5527) is in the
has been overhauled, remove the cylinder ACTION: Notice of proposed rulemaking
ADDRESSES section. Comments will be
assembly from service within the next 80 (NPRM).
operating hours TIS after the effective date of available in the AD docket shortly after
this AD. SUMMARY: We propose to adopt a new receipt.
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airworthiness directive (AD) for FOR FURTHER INFORMATION CONTACT:
(f) Installation Prohibitions
SOCATA Models TB 9, TB 10, TB 20, Albert J. Mercado, Aerospace Engineer,
After the effective date of this AD: FAA, Small Airplane Directorate, 901
TB 21, and TB 200 airplanes. This
(1) Do not repair, or reinstall onto any Locust, Room 301, Kansas City,
engine, any cylinder assembly removed per proposed AD results from mandatory
this AD. continuing airworthiness information Missouri 64106; telephone: (816) 329–
(2) Do not install any affected ECi cylinder (MCAI) originated by an aviation 4119; fax: (816) 329–4090; email:
assembly that has been overhauled, into any authority of another country to identify albert.mercado@faa.gov.
engine. and correct an unsafe condition on an SUPPLEMENTARY INFORMATION:
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Document Created: 2015-12-15 11:05:10
Document Modified: 2015-12-15 11:05:10
| 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 | Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. | |
| Dates | We must receive comments on this SNPRM by September 28, 2015. | |
| Contact | Jurgen E. Priester, Aerospace Engineer, Delegation Systems Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76137; phone: 817-222- 5190; fax: 817-222-5785; email: [email protected] | |
| FR Citation | 80 FR 52212 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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