83 FR 46853 - Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 180 (September 17, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 180 (September 17, 2018)
| Page Range | 46853-46857 | |
| FR Document | 2018-20142 |
[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)] [Rules and Regulations] [Pages 46853-46857] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-20142] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0479; Product Identifier 2016-NE-23-AD; Amendment 39-19369; AD 2018-17-15] RIN 2120-AA64 Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2018-02-14 for certain Honeywell International Inc. (Honeywell) TPE331 turboprop and TSE331 turboshaft engines. AD 2018-02-14 required inspection of the affected combustion chamber case assembly, replacement of those assemblies found cracked, and removal of affected assemblies on certain TPE331 and TSE331 engines. This AD retains the inspection and replacement requirements in AD 2018-02-04; revises the Applicability to add the TPE331-12 engine model and the related inspection action, correct references to certain engine models; and revises compliance to allow certain weld repair procedures. This AD was prompted by comments to revise the applicability and required actions of AD 2018-02-14 to include the TPE331-12B engine model, correct certain TPE engine model typographical errors, and to allow certain weld repair procedures. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 22, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 22, 2018. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of February 28, 2018 (83 FR 3263, January 24, 2018). ADDRESSES: For service information identified in this final rule, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ, 85034-2802; phone: 800-601-3099; website: 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-2018-0479. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.govby searching for and locating Docket No. FAA-2018- 0479; 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 [[Page 46854]] 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: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2018-02-14, Amendment 39-19167 (83 FR 3263, January 24, 2018), (``AD 2018-02-14''). AD 2018-02-14 applied to certain Honeywell TPE331 turboprop and TSE331 turboshaft engines. The NPRM published in the Federal Register on June 25, 2018 (83 FR 29479). The NPRM was prompted by comments to revise the applicability and required actions of AD 2018-02-14 to include the TPE331-12B engine model, correct certain TPE engine model typographical errors, and to allow certain weld repair procedures. The NPRM proposed to continue to require the inspection and replacement of the affected combustion chamber case assembly on certain TPE331 and TSE331 engines. The NPRM also proposed to revise the Applicability to include the TPE331-12B engine model and the related inspection action, correct references to the TPE331-43-A, -43-BL, -47-A, -55-B, and -61-A engine models, and to allow weld repair procedures to the applicable combustion chamber case assemblies provided those procedures are approved by the Manager, Los Angeles ACO Branch. 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. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed Honeywell Service Bulletin (SB) TPE331-72-2178, Revision 0, dated May 3, 2011 and Honeywell SB TPE331-72-2179, Revision 0, dated May 3, 2011. Honeywell SB TPE331-72-2178, Revision 0, describes procedures for inspection and removal of the affected combustion chamber case assemblies installed on all affected engines except for the TPE331-12B engine model. Honeywell SB TPE331-72-2179, Revision 0, describes procedures for inspection and removal of the affected combustion chamber case assemblies installed on the TPE331-12B engine model. 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. Other Related Service Information We reviewed Honeywell SBs TPE331-72-2228, Revision 0, dated June 12, 2014; TPE331-72-2230, Revision 0, dated June 19, 2014; TPE331-72- 2218, Revision 2, dated February 18, 2017; TPE331-72-2244, Revision 2, dated March 20 2017; TPE331-72-2235, Revision 2, dated February 18, 2017; TPE331-72-2281, Revision 0, dated July 22, 2016; TPE331-72-2294, Revision 0, dated December 22, 2016; TPE331-72-2231, Revision 1, dated August 1, 2017; and TSE331-72-2245, Revision 0, dated November 11, 2016. These SBs provide guidance on replacement of the affected combustion chamber case assemblies. Costs of Compliance We estimate that this AD affects 5,644 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- On-wing inspection............... 1 work-hour x $85 $0 $85 per inspection.. $479,740 per per hour = $85. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. We estimate that 158 engines will need this replacement during the first year of inspection. On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replacement of the combustion chamber case 1 work-hour x $85 per hour = $85 $15,000 $15,085 assembly. ---------------------------------------------------------------------------------------------------------------- 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. [[Page 46855]] This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, 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) 2018-02-14, Amendment 39-19167 (83 FR 3263, January 24, 2018), and adding the following new AD: 2018-17-15 Honeywell International Inc. (Type Certificate previously held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39-19369; Docket No. FAA-2018-0479; Product Identifier 2016-NE-23-AD. (a) Effective Date This AD is effective October 22, 2018. (b) Affected ADs This AD replaces AD 2018-02-14, Amendment 39-19167 (83 FR 3263, January 24, 2018). (c) Applicability This AD applies to Honeywell International Inc. (Honeywell) TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -8, -10, -10AV, -10GP, -10GT, -10N, -10P, -10R, -10T, -10U, -10UA, -10UF, - 10UG, -10UGR, -10UR, and -11U, -12B, -12JR, -12UA, -12UAR, -12UHR, - 25AA, -25AB, -25DA, -25DB, -25FA, -43-A, -43-B, -47-A, -55-B, and - 61-A turboprop engine models, including those engine models with a - L stamped after the model number (for example, -43-BL); and TSE331- 3U turboshaft engine models with combustion chamber case assemblies, part numbers (P/Ns) 869728-x, 893973-x, 3101668-x, and 3102613-x, where ``x'' denotes any dash number, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7240, Turbine Engine Combustion Section. (e) Unsafe Condition This AD was prompted by reports that combustion chamber case assemblies have cracked and ruptured. We are issuing this AD to prevent failure of the combustion chamber case assembly. The unsafe condition, if not addressed, could result in failure of the combustion chamber case assembly, in-flight shutdown, and reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For all affected engines: (i) Inspect all accessible areas of the combustion chamber case assembly, focusing on the weld joints, before accumulating 450 hours time in service (TIS) since last fuel nozzle inspection or within 50 hours TIS after the effective date of this AD, whichever occurs later. (ii) Perform the inspection in accordance with the Accomplishment Instructions, paragraphs 3.B.(1) through 3.B.(2), in Honeywell Service Bulletin (SB) TPE331-72-2178, Revision 0, dated May 3, 2011, or SB TPE331-72-2179, Revision 0, dated May 3, 2011, as applicable to the affected engine model. (iii) Thereafter, repeat this inspection during scheduled fuel nozzle inspections at intervals not to exceed 450 hours TIS since the last fuel nozzle inspection. (2) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A engine models with combustion chamber case assemblies, P/Ns 869728-1, 869728-3, or 893973-5, installed, and without the one-piece bleed pad with P3 boss; and for TPE331-1, -2, and -2UA engine models modified by National Flight Services, Inc., supplemental type certificate (STC) SE383CH, remove the combustion chamber case assembly from service at the next removal of the combustion chamber case assembly from the engine, not to exceed 3,700 hours TIS since last hot section inspection. (3) After the effective date of this AD, do not weld repair the applicable combustion chamber case assemblies unless the weld repair procedures are approved by the Manager, Los Angeles ACO Branch, and that approval specifically refers to this AD. (h) Definition (1) TPE331 engines modified by STC SE383CH may be defined as the ``Super 1'' and ``Super 2'' for the compressor modification of the TPE331-1 and the TPE331-2, -2U, and -2UA engine models, respectively. (2) Figures 1 and 2 to paragraph (h) of this AD illustrate the appearance of combustion chamber case assembly, P/N 893973-5, without and with, respectively, the one-piece bleed pad with the P3 boss. BILLING CODE 4910-13-P [[Page 46856]] [GRAPHIC] [TIFF OMITTED] TR17SE18.000 [GRAPHIC] [TIFF OMITTED] TR17SE18.001 BILLING CODE 4910-13-C (i) Installation Prohibition After the effective date of this AD, do not install a combustion chamber case assembly, P/N 869728-1, 869728-3, or 893973-5, in TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A engine models or in TPE331-1, -2, and -2UA engine models modified by National Flight Services, Inc., STC SE383CH, unless the combustion chamber case assembly has a one-piece bleed pad with P3 boss. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, 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: [email protected]. (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: [email protected]. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. [[Page 46857]] (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on October 22, 2018. (i) Honeywell International Inc. (Honeywell) Service Bulletin (SB) TPE331-72-2179, Revision 0, dated May 3, 2011. (ii) Reserved. (4) The following service information was approved for IBR on February 28, 2018 (83 FR 3263, January 24, 2018). (i) Honeywell SB TPE331-72-2178, Revision 0, dated May 3, 2011. (ii) Reserved. (5) For service information identified in this AD, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034- 2802; phone: 800-601-3099; website: https://myaerospace.honeywell.com/wps/portal. (6) You may view this service information at 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on September 5, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018-20142 Filed 9-14-18; 8:45 am] BILLING CODE 4910-13-P
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PART 229—AVAILABILITY OF FUNDS applies with respect to claims that the ACTION: Final rule.
AND COLLECTION OF CHECKS original check or to the electronic check or
(REGULATION CC) substitute check was altered or contained an SUMMARY: We are superseding
unauthorized signature. Airworthiness Directive (AD) 2018–02–
■ 1. The authority citation for part 229 2. The presumption of alteration applies 14 for certain Honeywell International
when the original check is unavailable for Inc. (Honeywell) TPE331 turboprop and
continues to read as follows: review by the banks in context of the dispute.
Authority: 12 U.S.C. 4001–4010, 12 U.S.C.
TSE331 turboshaft engines. AD 2018–
If the original check is produced, through
5001–5018. discovery or other means, and is made 02–14 required inspection of the
available for examination by all the parties, affected combustion chamber case
Subpart C—Collection of Checks the presumption no longer applies. assembly, replacement of those
3. This paragraph does not alter the assemblies found cracked, and removal
■ 2. In § 229.38, paragraph (i) is added transfer and presentment warranties under of affected assemblies on certain
to read as follows: the UCC that allocate liability among the TPE331 and TSE331 engines. This AD
parties to a check transaction with respect to retains the inspection and replacement
§ 229.38 Liability. an item that has been altered or that was requirements in AD 2018–02–04; revises
* * * * * issued with an unauthorized signature of the
the Applicability to add the TPE331–12
(i) Presumption of Alteration—(1) drawer. The UCC or other applicable check
law continues to apply with respect to other engine model and the related inspection
Presumption. Subject to paragraphs action, correct references to certain
(i)(2) and (3) of this section and in the rights, duties, and obligations related to
altered or unauthorized checks. In addition, engine models; and revises compliance
absence of a Federal statute or the presumption does not apply if it is to allow certain weld repair procedures.
regulation to the contrary, the contrary to another Federal statute or This AD was prompted by comments to
presumption in this paragraph applies regulation, such as the U.S. Treasury’s rules revise the applicability and required
with respect to any dispute between regarding U.S. Treasury checks. The actions of AD 2018–02–14 to include
banks arising under Federal or State law presumption of alteration may be varied by the TPE331–12B engine model, correct
as to whether a substitute check or agreement to the extent permitted under
certain TPE engine model typographical
electronic check transferred between § 229.37.
4. As stated in § 229.2, terms that are not errors, and to allow certain weld repair
those banks contains an alteration or is procedures. We are issuing this AD to
derived from an original check that was defined in that section have the meanings set
forth in the Uniform Commercial Code. address the unsafe condition on these
issued with an unauthorized signature ‘‘Alteration’’ is defined in UCC 3–407 and products.
of the drawer. When such a dispute includes both (i) an unauthorized change in
arises, there is a rebuttable presumption DATES: This AD is effective October 22,
a check that purports to modify in any
that the substitute check or electronic respect the obligation of a party, and (ii) an 2018.
check contains an alteration. unauthorized addition of words or numbers The Director of the Federal Register
(2) Rebuttal of presumption. The or other change to an incomplete check approved the incorporation by reference
presumption of alteration may be relating to the obligation of a party. of a certain publication listed in this AD
overcome by proving by a Alterations could include, for example, an as of October 22, 2018.
preponderance of evidence that either unauthorized change to a payee name or a The Director of the Federal Register
change to the date on a post-dated check that approved the incorporation by reference
the substitute check or electronic check purports to make the check currently
does not contain an alteration, or that of a certain other publication listed in
payable. ‘‘Unauthorized signature’’ is defined this AD as of February 28, 2018 (83 FR
the substitute check or electronic check in UCC 1–201 and further discussed in UCC
is derived from an original check that 3–403. An unauthorized signature could
3263, January 24, 2018).
was issued with an unauthorized include a forgery as well as a signature made ADDRESSES: For service information
signature of the drawer. without actual or apparent authority. identified in this final rule, contact
(3) Effect of producing original check. * * * * * Honeywell International Inc., 111 S 34th
If the original check is made available Street, Phoenix, AZ, 85034–2802;
By order of the Board of Governors of the
for examination by all banks involved in Federal Reserve System, September 11, 2018.
phone: 800–601–3099; website: https://
the dispute, the presumption in myaerospace.honeywell.com/wps/
Ann Misback,
paragraph (i)(1) of this section shall no portal. You may view this service
Secretary of the Board. information at the FAA, Engine and
longer apply.
[FR Doc. 2018–20029 Filed 9–14–18; 8:45 am] Propeller Standards Branch, 1200
■ 3. In appendix E, section XXIV, add
reserved paragraphs E through H and BILLING CODE 6210–01–P District Avenue, Burlington, MA 01803.
paragraph I to read as follows: For information on the availability of
this material at the FAA, call 781–238–
Appendix E to Part 229—Commentary DEPARTMENT OF TRANSPORTATION 7759. It is also available on the internet
* * * * * at http://www.regulations.gov by
Federal Aviation Administration searching for and locating Docket No.
XXIV. Section 229.38 Liability
FAA–2018–0479.
* * * * * 14 CFR Part 39
Examining the AD Docket
E through H [Reserved] [Docket No. FAA–2018–0479; Product
Identifier 2016–NE–23–AD; Amendment 39– You may examine the AD docket on
I. 229.38(i) Presumption of Alteration the internet at http://
19369; AD 2018–17–15]
1. This paragraph applies to disputes www.regulations.govby searching for
between banks where one bank has sent an RIN 2120–AA64 and locating Docket No. FAA–2018–
daltland on DSKBBV9HB2PROD with RULES
electronic check or a substitute check for 0479; or in person at Docket Operations
collection to the other bank. The Airworthiness Directives; Honeywell
presumption of alteration does not apply to International Inc. Turboprop and between 9 a.m. and 5 p.m., Monday
a dispute between banks where one bank sent Turboshaft Engines through Friday, except Federal holidays.
the original check to the other bank, even if The AD docket contains this final rule,
that check is subsequently truncated and AGENCY:Federal Aviation the regulatory evaluation, any
destroyed. The presumption of alteration Administration (FAA), DOT. comments received, and other
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This AD is issued in accordance with Authority: 49 U.S.C. 106(g), 40113, 44701. (f) Compliance
authority delegated by the Executive Comply with this AD within the
§ 39.13 [Amended]
Director, Aircraft Certification Service, compliance times specified, unless already
as authorized by FAA Order 8000.51C. ■ 2. The FAA amends § 39.13 by done.
In accordance with that order, issuance removing Airworthiness Directive (AD) (g) Required Actions
of ADs is normally a function of the 2018–02–14, Amendment 39–19167 (83 (1) For all affected engines:
Compliance and Airworthiness FR 3263, January 24, 2018), and adding (i) Inspect all accessible areas of the
Division, but during this transition the following new AD: combustion chamber case assembly, focusing
period, the Executive Director has on the weld joints, before accumulating 450
2018–17–15 Honeywell International Inc.
delegated the authority to issue ADs hours time in service (TIS) since last fuel
(Type Certificate previously held by
applicable to engines, propellers, and AlliedSignal Inc., Garrett Engine nozzle inspection or within 50 hours TIS
associated appliances to the Manager, Division; Garrett Turbine Engine after the effective date of this AD, whichever
Engine and Propeller Standards Branch, Company; and AiResearch occurs later.
Policy and Innovation Division. Manufacturing Company of Arizona): (ii) Perform the inspection in accordance
Amendment 39–19369; Docket No. with the Accomplishment Instructions,
Regulatory Findings FAA–2018–0479; Product Identifier paragraphs 3.B.(1) through 3.B.(2), in
We have determined that this AD will 2016–NE–23–AD. Honeywell Service Bulletin (SB) TPE331–72–
2178, Revision 0, dated May 3, 2011, or SB
not have federalism implications under (a) Effective Date TPE331–72–2179, Revision 0, dated May 3,
Executive Order 13132. This AD will 2011, as applicable to the affected engine
This AD is effective October 22, 2018.
not have a substantial direct effect on model.
the States, on the relationship between (b) Affected ADs (iii) Thereafter, repeat this inspection
the national government and the States, This AD replaces AD 2018–02–14, during scheduled fuel nozzle inspections at
or on the distribution of power and Amendment 39–19167 (83 FR 3263, January intervals not to exceed 450 hours TIS since
responsibilities among the various 24, 2018). the last fuel nozzle inspection.
levels of government. (2) For TPE331–3U, –3UW, –5, –5A, –5AB,
(c) Applicability –5B, –6, and –6A engine models with
For the reasons discussed above, I
This AD applies to Honeywell combustion chamber case assemblies, P/Ns
certify that this AD:
International Inc. (Honeywell) TPE331–1, –2, 869728–1, 869728–3, or 893973–5, installed,
(1) Is not a ‘‘significant regulatory –2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, and without the one-piece bleed pad with P3
action’’ under Executive Order 12866, –6A, –8, –10, –10AV, –10GP, –10GT, –10N, boss; and for TPE331–1, –2, and –2UA engine
(2) Is not a ‘‘significant rule’’ under –10P, –10R, –10T, –10U, –10UA, –10UF, models modified by National Flight Services,
DOT Regulatory Policies and Procedures –10UG, –10UGR, –10UR, and –11U, –12B, Inc., supplemental type certificate (STC)
(44 FR 11034, February 26, 1979), –12JR, –12UA, –12UAR, –12UHR, –25AA, SE383CH, remove the combustion chamber
(3) Will not affect intrastate aviation –25AB, –25DA, –25DB, –25FA, –43–A, –43– case assembly from service at the next
in Alaska, and B, –47–A, –55–B, and –61–A turboprop removal of the combustion chamber case
(4) Will not have a significant engine models, including those engine assembly from the engine, not to exceed
models with a -L stamped after the model 3,700 hours TIS since last hot section
economic impact, positive or negative,
number (for example, –43–BL); and TSE331– inspection.
on a substantial number of small entities (3) After the effective date of this AD, do
3U turboshaft engine models with
under the criteria of the Regulatory combustion chamber case assemblies, part not weld repair the applicable combustion
Flexibility Act. numbers (P/Ns) 869728–x, 893973–x, chamber case assemblies unless the weld
3101668–x, and 3102613–x, where ‘‘x’’ repair procedures are approved by the
List of Subjects in 14 CFR Part 39
denotes any dash number, installed. Manager, Los Angeles ACO Branch, and that
Air transportation, Aircraft, Aviation approval specifically refers to this AD.
safety, Incorporation by reference, (d) Subject
(h) Definition
Safety. Joint Aircraft System Component (JASC)
Code 7240, Turbine Engine Combustion (1) TPE331 engines modified by STC
Adoption of the Amendment Section. SE383CH may be defined as the ‘‘Super 1’’
and ‘‘Super 2’’ for the compressor
Accordingly, under the authority (e) Unsafe Condition modification of the TPE331–1 and the
delegated to me by the Administrator, This AD was prompted by reports that TPE331–2, –2U, and –2UA engine models,
the FAA amends 14 CFR part 39 as combustion chamber case assemblies have respectively.
follows: cracked and ruptured. We are issuing this AD (2) Figures 1 and 2 to paragraph (h) of this
to prevent failure of the combustion chamber AD illustrate the appearance of combustion
PART 39—AIRWORTHINESS case assembly. The unsafe condition, if not chamber case assembly,
DIRECTIVES addressed, could result in failure of the P/N 893973–5, without and with,
combustion chamber case assembly, in-flight respectively, the one-piece bleed pad with
■ 1. The authority citation for part 39 shutdown, and reduced control of the the P3 boss.
continues to read as follows: airplane. BILLING CODE 4910–13–P
daltland on DSKBBV9HB2PROD with RULES
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(2) You must use this service information pedal control system support box and repetitive detailed visual inspections of
as applicable to do the actions required by shaft and applicable corrective actions. the rudder pedal control system support
this AD, unless the AD specifies otherwise. We are issuing this AD to address the box and shaft and applicable corrective
(3) The following service information was
unsafe condition on these products. actions.
approved for IBR on October 22, 2018.
DATES: This AD is effective October 22, We are issuing this AD to address
(i) Honeywell International Inc.
(Honeywell) Service Bulletin (SB) TPE331– 2018. failure of the rudder pedal control
72–2179, Revision 0, dated May 3, 2011. The Director of the Federal Register system, which could result in reduced
(ii) Reserved. approved the incorporation by reference controllability of the airplane.
(4) The following service information was of a certain publication listed in this AD The European Aviation Safety Agency
approved for IBR on February 28, 2018 (83 as of October 22, 2018. (EASA), which is the Technical Agent
FR 3263, January 24, 2018). for the Member States of the European
(i) Honeywell SB TPE331–72–2178, ADDRESSES: For service information
Union, has issued EASA AD 2018–0051,
Revision 0, dated May 3, 2011. identified in this final rule, contact
dated March 2, 2018 (referred to after
(ii) Reserved. Airbus Defense and Space, Services/
this as the Mandatory Continuing
(5) For service information identified in Engineering support, Avenida de
this AD, contact Honeywell International
Airworthiness Information, or ‘‘the
Aragón 404, 28022 Madrid, Spain;
Inc., 111 S 34th Street, Phoenix, AZ 85034– MCAI’’), to correct an unsafe condition
phone: +34 91 585 55 84; fax: +34 91
2802; phone: 800–601–3099; website: https:// for certain Airbus Defense and Space
585 31 27; email:
myaerospace.honeywell.com/wps/portal. S.A. Model C–212–CB, C–212–CC, C–
MTA.TechnicalService@
(6) You may view this service information 212–CD, C–212–CE, and C–212–DF
at FAA, Engine and Propeller Standards military.airbus.com. You may view this
airplanes. The MCAI states:
Branch, 1200 District Avenue, Burlington, service information at the FAA,
MA 01803. For information on the Transport Standards Branch, 2200 Failures were reported of the rudder pedal
availability of this material at the FAA, call South 216th St., Des Moines, WA. For control system support on CASA C–212
781–238–7759. aeroplanes. Subsequent investigation
information on the availability of this revealed that the welding area of the affected
(7) You may view this service information material at the FAA, call 206–231–3195.
that is incorporated by reference at the support structure had broken.
It is also available on the internet at This condition, if not corrected, could lead
National Archives and Records
http://www.regulations.gov by searching to failure of the rudder [pedal] control
Administration (NARA). For information on
the availability of this material at NARA, call for and locating Docket No. FAA–2018– system, possibly resulting in reduced control
0552. of the aeroplane.
202–741–6030, or go to: http://
To address this potential unsafe condition,
www.archives.gov/federal-register/cfr/ibr- Examining the AD Docket EADS–CASA issued the SB [EADS–CASA
locations.html. Service Bulletin SB–212–27–0057, dated May
You may examine the AD docket on
Issued in Burlington, Massachusetts, on 21, 2014] to provide modification
September 5, 2018.
the internet at http:// instructions and EASA issued AD 2017–0036
www.regulations.gov by searching for [which corresponds to FAA AD 2017–19–08,
Robert J. Ganley,
and locating Docket No. FAA–2018– Amendment 39–19038 (82 FR 43835,
Manager, Engine and Propeller Standards 0552; or in person at Docket Operations September 20 2017) (‘‘AD 2017–19–08’’)] to
Branch, Aircraft Certification Service. require that modification [of the rudder pedal
between 9 a.m. and 5 p.m., Monday
[FR Doc. 2018–20142 Filed 9–14–18; 8:45 am] adjustment system]. During accomplishment
through Friday, except Federal holidays.
BILLING CODE 4910–13–P The AD docket contains this final rule, of that modification, several operators
reported difficulties or impossibility to
the regulatory evaluation, any follow the accomplishment instruction.
comments received, and other Consequently, EASA and Airbus D&S
DEPARTMENT OF TRANSPORTATION information. The address for Docket [Defense and Space S.A.] reviewed the
Federal Aviation Administration Operations (phone: 800–647–5527) is difficulty reports and decided that the
U.S. Department of Transportation, modification instructions have to be
Docket Operations, M–30, West improved.
14 CFR Part 39 Pending the improvement of the
Building Ground Floor, Room W12–140,
[Docket No. FAA–2018–0552; Product instructions of the SB [EADS–CASA Service
1200 New Jersey Avenue SE,
Identifier 2018–NM–049–AD; Amendment Bulletin SB–212–27–0057, dated May 21,
Washington, DC 20590. 2014] and in order to reduce the risk of
39–19402; AD 2018–19–02]
FOR FURTHER INFORMATION CONTACT: failure of the [rudder] pedal adjustment
RIN 2120–AA64 Shahram Daneshmandi, Aerospace system to an acceptable level, Airbus D&S
Engineer, International Section, issued the inspection AOT [Airbus Alert
Airworthiness Directives; Airbus Transport Standards Branch, FAA, 2200 Operators Transmission AOT–C212–27–
Defense and Space S.A. (Formerly South 216th St., Des Moines, WA 98198; 0002, dated February 28, 2018] to provide
Known as Construcciones instructions to repetitively inspect the
phone and fax: 206–231–3220. affected parts [rudder pedal support box Part
Aeronauticas, S.A. (CASA)) Airplanes SUPPLEMENTARY INFORMATION: Number (P/N) 212–46195.1 and shaft P/N
AGENCY: Federal Aviation 212–46120–20].
Discussion For the reasons described above, this
Administration (FAA), Department of
Transportation (DOT). We issued a notice of proposed [EASA] AD cancels the requirements of
rulemaking (NPRM) to amend 14 CFR EASA AD 2017–0036, which is superseded,
ACTION: Final rule. and requires repetitive [detailed visual]
part 39 by adding an AD that would
inspections of the rudder pedal adjustment
SUMMARY: We are adopting a new apply to certain Airbus Defense and system [rudder pedal support box P/N 212–
airworthiness directive (AD) for certain Space S.A. Model C–212–CB, C–212– 46195.1 and shaft P/N 212–46120–20] and,
Airbus Defense and Space S.A. Model CC, C–212–CD, C–212–CE, and C–212–
daltland on DSKBBV9HB2PROD with RULES
depending on findings, accomplishment of
C–212–CB, C–212–CC, C–212–CD, C– DF airplanes. The NPRM published in applicable corrective action(s).
212–CE, and C–212–DF airplanes. This the Federal Register on June 25, 2018 This [EASA] AD is considered to be an
AD was prompted by reports of failures (83 FR 29476). The NPRM was interim action and further [EASA] AD action
of the rudder pedal control system prompted by reports of failures of the may follow.
support. This AD requires repetitive rudder pedal control system support. Corrective actions include obtaining
detailed visual inspections of the rudder The NPRM proposed to require corrective actions approved by the
VerDate Sep<11>2014 16:03 Sep 14, 2018 Jkt 244001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\17SER1.SGM 17SER1](https://thefederalregister.org/doc/83_FR_47033/page/5.svg)
Document Created: 2018-09-15 01:37:15
Document Modified: 2018-09-15 01:37:15
| 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 October 22, 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 46853 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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