83 FR 55255 - Airworthiness Directives; Honeywell International Inc. Turboprop Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 214 (November 5, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 214 (November 5, 2018)
| Page Range | 55255-55258 | |
| FR Document | 2018-23775 |
[Federal Register Volume 83, Number 214 (Monday, November 5, 2018)] [Rules and Regulations] [Pages 55255-55258] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-23775] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0216; Product Identifier 1988-ANE-18-AD; Amendment 39-19474; AD 2018-22-01] RIN 2120-AA64 Airworthiness Directives; Honeywell International Inc. Turboprop Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 88-12-10 for certain Honeywell International Inc. (Honeywell) TPE331 turboprop engines. AD 88-12-10 required reducing the life limit for certain second stage turbine rotors. This AD requires removing certain second stage turbine rotors from service at a reduced life limit. This AD was prompted by report that a TPE331-11U engine experienced an uncontained rotor separation. In addition, cracks were discovered through eddy current inspection (ECI) in the bore of the second stage turbine rotor assembly after publication of AD 88-12-10. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 10, 2018. ADDRESSES: For service information identified in this final rule, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034-2802; phone: [[Page 55256]] 800-601-3099; internet: https://myaerospace.honeywell.com/wps/portal. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781- 238-7759. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0216. 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-2018- 0216; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647- 5527) is Document Operations, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-5210; email: joseph.costa@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 1988), (``AD 88-12-10''). AD 88-12-10 applied to Honeywell TPE331- 10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U turboprop engines equipped with 2nd stage turbine rotors, part numbers 3102106-1, -6, and -8, installed. The NPRM published in the Federal Register on June 20, 2018 (83 FR 28550). The NPRM was prompted by a report that a TPE331-11U engine installed on an M7 Aerospace LP SA227 airplane experienced an uncontained rotor separation. In addition, cracks were discovered through ECI in the bore of the second stage turbine rotor assembly after publication of AD 88-12-10. The NPRM proposed to remove certain second stage turbine rotors from service at a reduced life limit. We are issuing this AD to address the unsafe condition on these products. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Revise Compliance Times Honeywell requested that we remove from the NPRM the statement that the FAA finds that allowing an additional 100 cycles-in-service before their removal provides a sufficient level of safety for applicable second stage turbine rotors that have been in service for 30 years after the publication of AD 88-12-10. Honeywell indicated it believes that most of the IN100 rotors have been replaced at around 3,500 cycles during hot section inspection. Honeywell noted that the rotors would not make it to the next hot section inspection with a life of 4,800 cycles. Honeywell noted that there is a not a lot of field experience for IN100 rotors beyond 3,500 cycles. Honeywell commented that the removal schedule in the Honeywell service bulletin needs to remain the same (within 100 cycles-in-service for 3,301 to 4,000 cycles since new (CSN) rotors and within 50 cycles- in-service for 4,001 to 4,800 CSN rotors) since the event rotor failed at around 4,100 cycles. Additionally, Honeywell has also found rotors through eddy current inspection that had long cracks at around 4,300 cycles. We disagree. We would normally only require removal of parts within 50 cycles-in-service after the effective date of an AD when the risk justifies immediate action. The FAA assessed the risk of the affected rotors based on service experience and IN100 rotor propagation life of cracked and failed rotors. We found that the additional cycles in service allowed by this AD before the removal of the second stage turbine rotors provides an acceptable level of safety. We did not change this AD. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed. Related Service Information We reviewed Honeywell Service Bulletin (SB) TPE331-72-A2319, Revision 0, dated April 25, 2018, and TPE331-72-A2310, Revision 0, dated January 26, 2018. These SBs describe procedures for replacement of the second stage turbine rotor assembly installed on TPE331-8, -10, -10N, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U model engines. Costs of Compliance We estimate that this AD affects 100 engines installed on airplanes of U.S. registry. We estimate that 20 commercial engines and 80 general aviation engines will need this turbine rotor replacement to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Scheduled rotor replacement........... 1 work-hour x $85 per $7,500 $7,585 $379,250 hour = $85. Unscheduled rotor replacement......... 41 work-hours x $85 per 7,500 10,985 549,250 hour = $3,485. ---------------------------------------------------------------------------------------------------------------- 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, [[Page 55257]] as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings We have 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 above, 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, 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. 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 removing Airworthiness Directive (AD) 88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 1988), and adding the following new AD: 2018-22-01 Honeywell International Inc. (Type Certificate previously held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39-19474; Docket No. FAA-2018-0216; Product Identifier 1988-ANE-18-AD. (a) Effective Date This AD is effective December 10, 2018. (b) Affected ADs This AD replaces AD 88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 1988). (c) Applicability This AD applies to Honeywell International Inc. (Honeywell) TPE331-8, -10, -10N, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U turboprop engines with second stage turbine rotor assemblies, part number (P/Ns) 3102106-1, -6, and -8 or P/N 3101514- 1, -10 and -12, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by a report that a TPE331-11U engine installed on an M7 Aerospace LP SA227 airplane experienced an uncontained rotor separation and the discovery of cracks in the bore of the second stage turbine rotor assembly after publication of AD 88-12-10. We are issuing this AD to prevent failure of the second stage turbine rotor. The unsafe condition, if not addressed, could result in uncontained release of the second stage turbine rotor, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Remove from service the applicable second stage turbine rotor assembly, P/Ns 3102106-1, -6 and -8, according to the schedule in Table 1 to Paragraph (g)(1) of this AD: Table 1 to Paragraph (g)(1) of This AD--Removal of Second Stage Rotor, P/ Ns 3102106-1, -6 and -8 ------------------------------------------------------------------------ Second stage turbine rotor cycles since new (CSN) on the effective Removal schedule date of the AD ------------------------------------------------------------------------ 0 to 2,600........................ Prior to 3,000 CSN. 2,601 to 3,300.................... Within 400 cycles-in-service (CIS) after the effective date of this AD or 3,600 CSN, or at next access, whichever occurs first. 3,301 to 4,000.................... Within 200 cycles-in-service after the effective date of this AD or 4,100 CSN, or at next access, whichever occurs first. 4,001 to 4,800.................... Within 100 cycles-in-service after the effective date of this AD or 4,800 CSN, or at next access, whichever occurs first. ------------------------------------------------------------------------ (2) Remove from service the applicable second stage turbine rotor assembly, P/Ns 3101514-1, -10 and -12, per the schedule in Table 2 to Paragraph (g)(2) of this AD: Table 2 to Paragraph (g)(2) of This AD--Removal of Second Stage Rotors, P/Ns 3101514-1, -10 and -12 ------------------------------------------------------------------------ Second stage turbine rotor CSN on the effective date of the AD Removal schedule ------------------------------------------------------------------------ 0 to 2,600........................ Prior to 3,000 CSN. 2,601 to 3,200.................... Within 400 CIS after the effective date of this AD or 3,600 CSN, or at next access, whichever occurs first. 3,201 to 3,800.................... Within 200 CIS after the effective date of this AD or 4,100 CSN, or at next access, whichever occurs first. 3,801 to 4,400.................... Within 100 CIS after the effective date of this AD or 4,400 CSN, or at next access, whichever occurs first. ------------------------------------------------------------------------ [[Page 55258]] (h) Definition For the purpose of this AD, ``next access'' is defined as when the applicable second stage turbine rotor assembly is removed from the engine. (i) Installation Prohibition As of the effective date of this AD, do not install second stage turbine rotor assemblies, P/Ns 3102106-1, -6, and -8 and P/Ns 3101514-1, -10, and -12 on any engine. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (k) of this AD. You may email your request to: 9-ANM-LAACO-AMOC-REQUESTS@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (k) Related Information For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627- 5210; email: joseph.costa@faa.gov. (l) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on October 23, 2018. Karen M. Grant, Acting Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018-23775 Filed 11-2-18; 8:45 am] BILLING CODE 4910-13-P
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(h) Required Actions for this AD, if requested using the procedures (3) For service information identified in
If, during any inspection or records review found in 14 CFR 39.19. In accordance with this AD, contact Boeing Commercial
required by paragraph (g) of this AD, any ISS 14 CFR 39.19, send your request to your Airplanes, Attention: Contractual & Data
OPS P/N COL40–0010–0100 or COL46– principal inspector or local Flight Standards Services (C&DS), 2600 Westminster Blvd.,
0007–0100 is found: Within 12 months after District Office, as appropriate. If sending MC 110–SK57, Seal Beach, CA 90740–5600;
the effective date of this AD, do all applicable information directly to the manager of the telephone 562–797–1717; internet https://
actions identified as ‘‘RC’’ (required for certification office, send it to the attention of www.myboeingfleet.com.
compliance) in, and in accordance with, the the person identified in paragraph (m)(1) of (4) You may view this service information
Accomplishment Instructions of Boeing Alert this AD. Information may be emailed to: 9- at the FAA, Transport Standards Branch,
Service Bulletin B787–81205–SB340036–00, ANM-Seattle-ACO-AMOC-Requests@faa.gov. 2200 South 216th St., Des Moines, WA. For
Issue 001, dated June 30, 2017; except where (2) Before using any approved AMOC, information on the availability of this
Boeing Alert Service Bulletin B787–81205– notify your appropriate principal inspector, material at the FAA, call 206–231–3195.
SB340036–00, Issue 001, dated June 30, 2017, or lacking a principal inspector, the manager (5) You may view this service information
specifies installing software P/Ns COL41– of the local flight standards district office/ that is incorporated by reference at the
0010–0101 and COL44–0007–0102, this AD certificate holding district office. National Archives and Records
requires installing P/Ns COL41–0010–0101 (3) An AMOC that provides an acceptable Administration (NARA). For information on
and COL44–0007–0102, or later-approved level of safety may be used for any repair, the availability of this material at NARA, call
software versions. Later-approved software modification, or alteration required by this 202–741–6030, or go to: http://
versions are only those Boeing software AD if it is approved by the Boeing www.archives.gov/federal-register/cfr/ibr-
versions that are approved as a replacement Commercial Airplanes ODA that has been locations.html.
for the applicable software, and are approved authorized by the Manager, Seattle ACO
as part of the type design by the FAA or the Issued in Des Moines, Washington, on
Branch, to make those findings. To be
Boeing Commercial Airplanes Organization October 22, 2018.
approved, the repair method, modification
Designation Authorization (ODA) after deviation, or alteration deviation must meet Michael Kaszycki,
issuance of Boeing Alert Service Bulletin the certification basis of the airplane, and the Acting Director, System Oversight Division,
B787–81205–SB340036–00, Issue 001, dated approval must specifically refer to this AD. Aircraft Certification Service.
June 30, 2017. (4) For service information that contains [FR Doc. 2018–23690 Filed 11–2–18; 8:45 am]
(i) Additional Actions for Group 1 Airplanes steps that are labeled as RC, the provisions BILLING CODE 4910–13–P
of paragraphs (l)(4)(i) and (l)(4)(ii) of this AD
For Group 1 airplanes identified in Boeing apply.
Alert Service Bulletin B787–81205– (i) The steps labeled as RC, including
SB340036–00, Issue 001, dated June 30, 2017: DEPARTMENT OF TRANSPORTATION
substeps under an RC step and any figures
Prior to accomplishment of the actions identified in an RC step, must be done to
required by paragraph (h) of this AD, install Federal Aviation Administration
comply with the AD. If a step or substep is
new software for the ISS OPS, ISS option
labeled ‘‘RC Exempt,’’ then the RC
selection software (OSS) file, and ISS airline 14 CFR Part 39
requirement is removed from that step or
selectable option (ASO) file; and install a
substep. An AMOC is required for any [Docket No. FAA–2018–0216; Product
new ISS definition file database within the
deviations to RC steps, including substeps Identifier 1988–ANE–18–AD; Amendment
displays and crew alerting (DCA) system; in
and identified figures. 39–19474; AD 2018–22–01]
accordance with the Accomplishment
(ii) Steps not labeled as RC may be
Instructions of Boeing Service Bulletin B787– RIN 2120–AA64
deviated from using accepted methods in
81205–SB340005–00, Issue 002, dated April
accordance with the operator’s maintenance
27, 2016; except where Boeing Service
or inspection program without obtaining Airworthiness Directives; Honeywell
Bulletin B787–81205–SB340005–00, Issue
002, dated April 27, 2016, specifies installing approval of an AMOC, provided the RC steps, International Inc. Turboprop Engines
certain software, this AD requires installing including substeps and identified figures, can
still be done as specified, and the airplane AGENCY: Federal Aviation
that software or later-approved software Administration (FAA), DOT.
versions. Later-approved software versions can be put back in an airworthy condition.
are only those Boeing software versions that ACTION: Final rule.
(m) Related Information
are approved as a replacement for the
applicable software, and are approved as part
(1) For more information about this AD, SUMMARY: We are superseding
contact Nelson O. Sanchez, Aerospace Airworthiness Directive (AD) 88–12–10
of the type design by the FAA or the Boeing
Engineer, Systems and Equipment Section, for certain Honeywell International Inc.
Commercial Airplanes ODA after issuance of
Boeing Service Bulletin B787–81205– FAA, Seattle ACO Branch, 2200 South 216th (Honeywell) TPE331 turboprop engines.
St., Des Moines, WA 98198; phone and fax:
SB340005–00, Issue 002, dated April 27, AD 88–12–10 required reducing the life
2016. 206–231–3543; email: nelson.sanchez@
faa.gov. limit for certain second stage turbine
(j) Parts Installation Prohibition (2) Service information identified in this rotors. This AD requires removing
As of the effective date of this AD, no AD that is not incorporated by reference is certain second stage turbine rotors from
person may install ISS OPS part number available at the addresses specified in service at a reduced life limit. This AD
COL40–0010–0100 or COL46–0007–0100 on paragraphs (n)(3) and (n)(4) of this AD. was prompted by report that a TPE331–
any airplane, except in accomplishment of (n) Material Incorporated by Reference 11U engine experienced an uncontained
the actions required by paragraph (i) of this rotor separation. In addition, cracks
AD. (1) The Director of the Federal Register
were discovered through eddy current
approved the incorporation by reference
(k) Credit for Previous Actions (IBR) of the service information listed in this inspection (ECI) in the bore of the
This paragraph provides credit for the paragraph under 5 U.S.C. 552(a) and 1 CFR second stage turbine rotor assembly
actions specified in paragraph (i) of this AD, part 51. after publication of AD 88–12–10. We
if those actions were performed before the (2) You must use this service information are issuing this AD to address the unsafe
effective date of this AD using Boeing Service as applicable to do the actions required by condition on these products.
Bulletin B787–81205–SB340005–00, Issue this AD, unless the AD specifies otherwise. DATES: This AD is effective December
001, dated December 11, 2015. (i) Boeing Alert Service Bulletin B787– 10, 2018.
81205–SB340036–00, Issue 001, dated June
(l) Alternative Methods of Compliance 30, 2017. ADDRESSES: For service information
(AMOCs) (ii) Boeing Service Bulletin B787–81205– identified in this final rule, contact
(1) The Manager, Seattle ACO Branch, SB340005–00, Issue 002, dated April 27, Honeywell International Inc., 111 S 34th
FAA, has the authority to approve AMOCs 2016. Street, Phoenix, AZ 85034–2802; phone:
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as authorized by FAA Order 8000.51C. List of Subjects in 14 CFR Part 39 (c) Applicability
In accordance with that order, issuance Air transportation, Aircraft, Aviation This AD applies to Honeywell
of ADs is normally a function of the safety, Incorporation by reference, International Inc. (Honeywell) TPE331–8,
Compliance and Airworthiness Safety. –10, –10N, –10R, –10U, –10UA, –10UF,
Division, but during this transition –10UG, –10UGR, –10UR, and –11U
period, the Executive Director has Adoption of the Amendment turboprop engines with second stage turbine
delegated the authority to issue ADs Accordingly, under the authority rotor assemblies, part number (P/Ns)
applicable to engines, propellers, and delegated to me by the Administrator, 3102106–1, –6, and –8 or P/N 3101514–1,
associated appliances to the Manager, the FAA amends 14 CFR part 39 as –10 and –12, installed.
Engine and Propeller Standards Branch, follows: (d) Subject
Policy and Innovation Division. Joint Aircraft System Component (JASC)
PART 39—AIRWORTHINESS
Regulatory Findings DIRECTIVES Code 7250, Turbine Section.
■ 1. The authority citation for part 39 (e) Unsafe Condition
We have determined that this AD will
not have federalism implications under continues to read as follows: This AD was prompted by a report that a
Executive Order 13132. This AD will Authority: 49 U.S.C. 106(g), 40113, 44701. TPE331–11U engine installed on an M7
not have a substantial direct effect on Aerospace LP SA227 airplane experienced an
§ 39.13 [Amended] uncontained rotor separation and the
the States, on the relationship between
■ 2. The FAA amends § 39.13 by discovery of cracks in the bore of the second
the national government and the States,
removing Airworthiness Directive (AD) stage turbine rotor assembly after publication
or on the distribution of power and
88–12–10, Amendment 39–5910 (53 FR of AD 88–12–10. We are issuing this AD to
responsibilities among the various prevent failure of the second stage turbine
levels of government. 19766, May 31, 1988), and adding the
following new AD: rotor. The unsafe condition, if not addressed,
For the reasons discussed above, I could result in uncontained release of the
certify that this AD: 2018–22–01 Honeywell International Inc. second stage turbine rotor, damage to the
(Type Certificate previously held by
(1) Is not a ‘‘significant regulatory engine, and damage to the airplane.
AlliedSignal Inc., Garrett Engine
action’’ under Executive Order 12866, Division; Garrett Turbine Engine (f) Compliance
Company; and AiResearch
(2) Is not a ‘‘significant rule’’ under Manufacturing Company of Arizona): Comply with this AD within the
DOT Regulatory Policies and Procedures Amendment 39–19474; Docket No. compliance times specified, unless already
(44 FR 11034, February 26, 1979), FAA–2018–0216; Product Identifier done.
(3) Will not affect intrastate aviation 1988–ANE–18–AD.
(g) Required Actions
in Alaska, and (a) Effective Date (1) Remove from service the applicable
(4) Will not have a significant This AD is effective December 10, 2018. second stage turbine rotor assembly, P/Ns
economic impact, positive or negative, (b) Affected ADs 3102106–1, –6 and –8, according to the
on a substantial number of small entities schedule in Table 1 to Paragraph (g)(1) of this
This AD replaces AD 88–12–10,
under the criteria of the Regulatory Amendment 39–5910 (53 FR 19766, May 31, AD:
Flexibility Act. 1988).
TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD—REMOVAL OF SECOND STAGE ROTOR, P/NS 3102106–1, –6 AND –8
Second stage turbine rotor cycles
since new (CSN) on the effective Removal schedule
date of the AD
0 to 2,600 ........................................ Prior to 3,000 CSN.
2,601 to 3,300 ................................. Within 400 cycles-in-service (CIS) after the effective date of this AD or 3,600 CSN, or at next access,
whichever occurs first.
3,301 to 4,000 ................................. Within 200 cycles-in-service after the effective date of this AD or 4,100 CSN, or at next access, whichever
occurs first.
4,001 to 4,800 ................................. Within 100 cycles-in-service after the effective date of this AD or 4,800 CSN, or at next access, whichever
occurs first.
(2) Remove from service the –12, per the schedule in Table 2 to
applicable second stage turbine rotor Paragraph (g)(2) of this AD:
assembly, P/Ns 3101514–1, –10 and
TABLE 2 TO PARAGRAPH (g)(2) OF THIS AD—REMOVAL OF SECOND STAGE ROTORS, P/NS 3101514–1, –10 AND –12
Second stage turbine rotor CSN on Removal schedule
the effective date of the AD
0 to 2,600 ........................................ Prior to 3,000 CSN.
2,601 to 3,200 ................................. Within 400 CIS after the effective date of this AD or 3,600 CSN, or at next access, whichever occurs first.
3,201 to 3,800 ................................. Within 200 CIS after the effective date of this AD or 4,100 CSN, or at next access, whichever occurs first.
3,801 to 4,400 ................................. Within 100 CIS after the effective date of this AD or 4,400 CSN, or at next access, whichever occurs first.
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(h) Definition 10 airplanes. This AD results from of the European Community, issued
For the purpose of this AD, ‘‘next access’’ mandatory continuing airworthiness EASA AD No. 2018–0030, dated January
is defined as when the applicable second information (MCAI) issued by an 31, 2018 (referred to after this as ‘‘the
stage turbine rotor assembly is removed from aviation authority of another country to MCAI’’). The MCAI states that:
the engine. identify and correct an unsafe condition During a scheduled maintenance
(i) Installation Prohibition on an aviation product. The MCAI inspection, cracks were found on the wing
As of the effective date of this AD, do not describes the unsafe condition as fatigue front attachments of a TB 10 aeroplane.
install second stage turbine rotor assemblies, cracking of the wing front attachments This condition, if not detected and
P/Ns 3102106–1, –6, and –8 and P/Ns on the wing and fuselage sides. We are corrected, could affect the structural integrity
3101514–1, –10, and –12 on any engine. issuing this AD to require actions to of the aeroplane.
address the unsafe condition on these Prompted by these findings, SOCATA
(j) Alternative Methods of Compliance issued SB 10–081–57 to provide inspection
(AMOCs)
products.
and modification instructions, and DGAC
(1) The Manager, Los Angeles ACO, FAA, DATES: This AD is effective December France issued AD 94–264(A), later revised, to
has the authority to approve AMOCs for this 10, 2018. require repetitive inspections of wing front
AD, if requested using the procedures found The Director of the Federal Register attachments of TB 9 and TB 10 aeroplanes
in 14 CFR 39.19. In accordance with 14 CFR approved the incorporation by reference (all MSN up to 822 inclusive, with some
39.19, send your request to your principal of a certain publication listed in the AD excluded). That [DGAC France] AD also
inspector or local Flight Standards District as of December 10, 2018. required installation of reinforcement kits,
Office, as appropriate. If sending information applied as repair (if cracks were found) or as
ADDRESSES: You may examine the AD
directly to the manager of the certification modification (if no cracks were found), of the
office, send it to the attention of the person docket on the internet at http:// wing front attachments, on both wing and
identified in paragraph (k) of this AD. You www.regulations.gov by searching for fuselage sides, and repetitive replacement of
may email your request to: 9-ANM-LAACO- and locating Docket No. FAA–2018– those reinforcements afterwards.
AMOC-REQUESTS@faa.gov. 0326; or in person at Docket Operations, Since DGAC France AD 94–264(A) R1 was
(2) Before using any approved AMOC, U.S. Department of Transportation, issued, cracks have been found on wing front
notify your appropriate principal inspector, Docket Operations, M–30, West attachments, on the wing side, on TB10
or lacking a principal inspector, the manager Building Ground Floor, Room W12–140, aeroplanes to which the AD did not apply,
of the local flight standards district office/ i.e. which were not subject to repetitive
1200 New Jersey Avenue SE,
certificate holding district office. inspections as required by that [DGAC
Washington, DC 20590. France] AD. Consequently, SOCATA revised
(k) Related Information For service information identified in SB 10–081–57 (now at revision (rev) 3),
For more information about this AD, this AD, contact SOCATA, Direction des extending the Applicability to all TB 10
contact Joseph Costa, Aerospace Engineer, services, 65921 Tarbes Cedex 9, France; aeroplanes, as well as to TB 200 aeroplanes,
Los Angeles ACO Branch, FAA, 3960 phone: +33 (0) 5 62 41 73 00; fax: +33 and improving the repair solution of the wing
Paramount Blvd., Lakewood, CA 90712– (0) 5 62 41 76 54; email: info@ front attachment on wing side.
4137; phone: 562–627–5246; fax: 562–627– socata.daher.com; internet: https:// For the reason described above, this
5210; email: joseph.costa@faa.gov. www.mysocata.com/login/accueil.php. [EASA] AD retains the requirements of DGAC
(l) Material Incorporated by Reference You may view this referenced service France AD 94–264(A) R1, which is
superseded, expands the Applicability to all
None. information at the FAA, Policy and
MSN for TB 9 and TB 10 aeroplanes and
Innovation Division, 901 Locust, Kansas includes TB 200 aeroplanes, and requires an
Issued in Burlington, Massachusetts, on
October 23, 2018.
City, Missouri 64106. For information improved repair solution of the wing front
on the availability of this material at the attachment on wing side.
Karen M. Grant,
FAA, call (816) 329–4148. It is also
Acting Manager, Engine and Propeller The MCAI can be found in the AD
available on the internet at http://
Standards Branch, Aircraft Certification docket on the internet at: https://
www.regulations.gov by searching for
Service. www.regulations.gov/document?D=
Docket No. FAA–2018–0326.
[FR Doc. 2018–23775 Filed 11–2–18; 8:45 am] FAA-2018-0326-0003.
FOR FURTHER INFORMATION CONTACT:
BILLING CODE 4910–13–P
Quentin Coon, Aerospace Engineer, 901 Comments
Locust, Room 301, Kansas City, We gave the public the opportunity to
DEPARTMENT OF TRANSPORTATION Missouri 64106; telephone: (816) 329– participate in developing this AD. The
4168; fax: (816) 329–4090; email: following presents the comment
Federal Aviation Administration quentin.coon@faa.gov. received on the proposal and the FAA’s
SUPPLEMENTARY INFORMATION: response to the comment.
14 CFR Part 39 Discussion Request for an Explanation of
[Docket No. FAA–2018–0326; Product We issued a notice of proposed Compliance Time
Identifier 2018–CE–006–AD; Amendment
rulemaking (NPRM) to amend 14 CFR Daher requested that we explain why
39–19464; AD 2018–21–06]
part 39 to supersede AD 98–16–03, the compliance times in the NPRM are
RIN 2120–AA64 Amendment 39–10677 (63 FR 40359, presented in landings and do not match
July 29, 1998) (‘‘AD 98–16–03’’). The the compliance times in the EASA AD,
Airworthiness Directives; SOCATA NPRM was published in the Federal which uses both hours time-in-service
Airplanes Register on May 9, 2018 (83 FR 21199), (TIS) and number of landings.
AGENCY: Federal Aviation and proposed to correct an unsafe The NPRM retained the compliance
Administration (FAA), Department of condition for SOCATA Model TB 9, times from AD 98–16–03, which were
Transportation (DOT). Model TB 10, and Model TB 200 based in landings instead of hours TIS.
ACTION: Final rule. airplanes. We based the NPRM on MCAI The NPRM also retained the formula for
originated by an aviation authority of converting hours TIS to landings from
SUMMARY: We are superseding another country. The European Aviation AD 98–16–03 for airplanes with an
Airworthiness Directive (AD) 98–16–03 Safety Agency (EASA), which is the unknown number of landings. Because
for SOCATA Model TB 9 and Model TB Technical Agent for the Member States we also retained the effective date of AD
VerDate Sep<11>2014 16:30 Nov 02, 2018 Jkt 247001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\05NOR1.SGM 05NOR1](https://thefederalregister.org/doc/83_FR_55469/page/4.svg)
Document Created: 2018-11-03 00:28:38
Document Modified: 2018-11-03 00:28:38
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective December 10, 2018. | |
| Contact | Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 83 FR 55255 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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