83 FR 55619 - Airworthiness Directives; International Aero Engines Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 216 (November 7, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 216 (November 7, 2018)
| Page Range | 55619-55626 | |
| FR Document | 2018-24250 |
[Federal Register Volume 83, Number 216 (Wednesday, November 7, 2018)] [Rules and Regulations] [Pages 55619-55626] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-24250] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0431; Product Identifier 2018-NE-16-AD; Amendment 39-19475; AD 2018-22-02] RIN 2120-AA64 Airworthiness Directives; International Aero Engines Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all International Aero Engines (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM, and PW1122G-JM turbofan engines with a certain high-pressure compressor (HPC) front hub installed. This AD was prompted by corrosion found on the HPC front hub. This AD requires replacing the HPC front hub with a part eligible for installation. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 12, 2018. ADDRESSES: For service information identified in this final rule, contact International Aero Engines (IAE), 400 Main Street, East Hartford, CT, 06118; phone: 800-565-0140; email: [email protected]; internet: http://fleetcare.pw.utc.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 [[Page 55620]] 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-2018-0431. 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- 0431; 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 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: Kevin M. Clark, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 781-238-7088; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to IAE PW1133G-JM, PW1133GA- JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM, and PW1122G-JM turbofan engines with a certain HPC front hub installed. The NPRM published in the Federal Register on June 28, 2018 (83 FR 30370). The NPRM was prompted by a report that corrosion was found on HPC front hub, part number (P/N) 30G2401. The HPC front hub exhibited deposits that could not be removed using standard procedures and worsened over time. After further investigation, pitting corrosion was found below the painted surface. This condition, if not addressed, could result in uncontained HPC front hub release, damage to the engine, and damage to the airplane. The NPRM proposed to require replacing the HPC front hub with a part eligible for installation. 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 final rule. We have considered the comment received on the NPRM and the FAA's response to each comment. Request Clarification on CSN Limit All Nippon Airways requested that we clarify which cycles since new (CSN) limit for this AD is correct. ANA stated the PW Service Bulletin PW1000G-C-72-00-0106-00A-930A-D, dated June 15, 2018 specifies a limit of 4,400 cycles since new (CSN), while paragraph (g) of this AD specifies a limit of 4,440 CSN. We disagree. The AD limit of 4,440 CSN is correct. We found that 4,440 CSN provides an acceptable level of safety, and reducing the CSN limit in this AD to match the SB is not required. Therefore, 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 final rule 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 We reviewed Section PW1000G-C-05-10-00-02A-288A-D of the PW1100G-JM Series Airworthiness Limitations Manual, P/N 5316993, dated September 30, 2015. Section PW1000G-C-05-10-00-02A-288A-D provides guidance for an approved FAA method of mixed model cycles since new calculation. Costs of Compliance We estimate that this AD affects 16 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Replace HPC front hub................. 0 work-hours x $85 per $11,600 $11,600 $185,600 hour = $85. ---------------------------------------------------------------------------------------------------------------- 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, 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 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 [[Page 55621]] (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 adding the following new airworthiness directive (AD): AD 2018-22-02 International Aero Engines: Amendment 39-19475; Docket No. FAA-2018-0431; Product Identifier 2018-NE-16-AD. (a) Effective Date This AD is effective December 12, 2018. (b) Affected ADs None. (c) Applicability This AD applies to International Aero Engines (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1-JM, and PW1122G-JM turbofan engines with a high-pressure compressor (HPC) front hub, part number (P/N) 30G2401, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by corrosion found on the HPC front hub, P/ N 30G2401, installed. We are issuing this AD to prevent cracking and failure of the HPC front hub. The unsafe condition, if not addressed, could result in uncontained HPC front hub release, 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 Remove from service the HPC front hub, P/N 30G2401, within 120 days after the effective date of this AD, or as follows, whichever occurs later, and replace with a part eligible for installation: (1) For PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G1-JM, PW1127GA-JM, and PW1127G-JM engines, remove the HPC front hub before exceeding 6,180 cycles since new (CSN) or within five years since the ship date listed in Table 1 to paragraph (g) of this AD, whichever occurs first. (2) For PW1130G-JM, PW1133GA-JM, and PW1133G-JM engines, remove the HPC front hub before exceeding 4,440 CSN or within four years since the ship date listed in Table 1 to paragraph (g) of this AD, whichever occurs first. (3) For engines operating as a mix of models listed in paragraphs (g)(1) and (2) of this AD, remove the HPC front hub using a CSN calculated by an approved FAA method or within four years since the ship date listed in Table 1 to paragraph (g) of this AD, whichever occurs first. You may find guidance for an approved FAA method of mixed model CSN calculation in Section PW1000G-C-05-10-00- 02A-288A-D of the PW1100G-JM Series Airworthiness Limitations Manual, P/N 5316993, dated September 30, 2015. (4) For any HPC front hub, P/N 30G2401, whose serial number is not listed in Table 1 to paragraph (g) of this AD, use October 21, 2015, as the ship date. BILLING CODE 4910-13-P [[Page 55622]] [GRAPHIC] [TIFF OMITTED] TR07NO18.001 [[Page 55623]] [GRAPHIC] [TIFF OMITTED] TR07NO18.002 [[Page 55624]] [GRAPHIC] [TIFF OMITTED] TR07NO18.003 [[Page 55625]] [GRAPHIC] [TIFF OMITTED] TR07NO18.004 [[Page 55626]] [GRAPHIC] [TIFF OMITTED] TR07NO18.005 BILLING CODE 4910-13-C (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO 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 (i) 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. (i) Related Information For more information about this AD, contact Kevin M. Clark, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 781-238-7088; fax: 781-238-7199; email: [email protected]. (j) Material Incorporated by Reference None. Issued in Burlington, MA, on November 01, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018-24250 Filed 11-6-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations 55619
2018–22–13 Airbus SAS: Amendment 39– has the authority to approve AMOCs for this telephone +33 5 61 93 36 96; fax +33 5 61
19486; Docket No. FAA–2018–0908; AD, if requested using the procedures found 93 45 80; email continued-
Product Identifier 2018–NM–136–AD. in 14 CFR 39.19. In accordance with 14 CFR airworthiness.a350@airbus.com; internet
39.19, send your request to your principal http://www.airbus.com.
(a) Effective Date (4) You may view this service information
inspector or local Flight Standards District
This AD becomes effective November 23, Office, as appropriate. If sending information at the FAA, Transport Standards Branch,
2018. directly to the International Section, send it 2200 South 216th St., Des Moines, WA. For
to the attention of the person identified in information on the availability of this
(b) Affected ADs
paragraph (i)(2) of this AD. Information may material at the FAA, call 206–231–3195.
None. be emailed to 9-ANM-116-AMOC- (5) You may view this service information
(c) Applicability REQUESTS@faa.gov. Before using any that is incorporated by reference at the
approved AMOC, notify your appropriate National Archives and Records
This AD applies to Airbus SAS Model principal inspector, or lacking a principal Administration (NARA). For information on
A350–941 and -1041 airplanes, certificated in inspector, the manager of the local flight the availability of this material at NARA, call
any category, except those on which the 202–741–6030, or go to: http://
standards district office/certificate holding
modifications specified in paragraph (c)(1) or www.archives.gov/federal-register/cfr/ibr-
district office.
(c)(2) of this AD, as applicable, have been locations.html.
(2) Contacting the Manufacturer: For any
embodied in production.
requirement in this AD to obtain corrective Issued in Des Moines, Washington, on
(1) Airbus modifications 113759 and
actions from a manufacturer, the action must October 22, 2018.
113758.
be accomplished using a method approved
(2) Airbus modifications 113760 and Michael Kaszycki,
by the Manager, International Section,
113758. Acting Director, System Oversight Division,
Transport Standards Branch, FAA; or the
(d) Subject European Aviation Safety Agency (EASA); or Aircraft Certification Service.
Airbus SAS’s EASA Design Organization [FR Doc. 2018–23991 Filed 11–6–18; 8:45 am]
Air Transport Association (ATA) of
America Code 27, Flight controls. Approval (DOA). If approved by the DOA, BILLING CODE 4910–13–P
the approval must include the DOA-
(e) Reason authorized signature.
This AD was prompted by a technical issue (3) Required for Compliance (RC): If any DEPARTMENT OF TRANSPORTATION
detected on the inboard aileron electro- service information contains procedures or
hydrostatic actuators that caused potential tests that are identified as RC, those Federal Aviation Administration
erroneous monitoring of those actuators. We procedures and tests must be done to comply
are issuing this AD to address possible in- with this AD; any procedures or tests that are
14 CFR Part 39
flight loss of inboard aileron control, not identified as RC are recommended. Those
consequent increased fuel consumption due procedures and tests that are not identified [Docket No. FAA–2018–0431; Product
to the resulting drag, and reduced control or as RC may be deviated from using accepted Identifier 2018–NE–16–AD; Amendment 39–
performance of the airplane if one engine is methods in accordance with the operator’s 19475; AD 2018–22–02]
also inoperative. maintenance or inspection program without
obtaining approval of an AMOC, provided RIN 2120–AA64
(f) Compliance the procedures and tests identified as RC can
Comply with this AD within the be done and the airplane can be put back in Airworthiness Directives; International
compliance times specified, unless already an airworthy condition. Any substitutions or Aero Engines Turbofan Engines
done. changes to procedures or tests identified as
AGENCY: Federal Aviation
RC require approval of an AMOC.
(g) Revision of the Airplane Flight Manual Administration (FAA), DOT.
(AFM) (i) Related Information ACTION: Final rule.
Within 30 days after the effective date of (1) Refer to Mandatory Continuing
this AD, revise the Abnormal Procedures Airworthiness Information (MCAI) EASA SUMMARY: We are adopting a new
section of the AFM to include the Airworthiness Directive 2018–0213, dated airworthiness directive (AD) for all
information in Airbus A350 Temporary October 1, 2018, for related information. This International Aero Engines (IAE)
Revision (TR) 113, Issue 1.0, dated July 27, MCAI may be found in the AD docket on the PW1133G–JM, PW1133GA–JM,
2018, which introduces updated procedures internet at http://www.regulations.gov by PW1130G–JM, PW1127G–JM,
related to inboard aileron fault operations. searching for and locating Docket No. FAA– PW1127GA–JM, PW1127G1–JM,
This may be done by inserting a copy of TR 2018–0908. PW1124G–JM, PW1124G1–JM, and
113, Issue 1.0, dated July 27, 2018, into the (2) For more information about this AD,
AFM. When TR 113, Issue 1.0, dated July 27, contact Kathleen Arrigotti, Aerospace
PW1122G–JM turbofan engines with a
2018, has been included in general revisions Engineer, International Section, Transport certain high-pressure compressor (HPC)
of the AFM, the general revisions may be Standards Branch, FAA, 2200 South 216th front hub installed. This AD was
inserted into the AFM, provided the relevant St., Des Moines, WA 98198; telephone and prompted by corrosion found on the
information in the general revisions is fax 206–231–3218. HPC front hub. This AD requires
identical to that in TR 113, Issue 1.0, dated
(j) Material Incorporated by Reference
replacing the HPC front hub with a part
July 27, 2018, and the TR may be removed. eligible for installation. We are issuing
Operate the airplane according to the (1) The Director of the Federal Register this AD to address the unsafe condition
procedures in TR 113, Issue 1.0, dated July approved the incorporation by reference
(IBR) of the service information listed in this
on these products.
27, 2018. In case any discrepancy is
identified between procedures displayed on paragraph under 5 U.S.C. 552(a) and 1 CFR DATES: This AD is effective December
the electronic centralized aircraft monitoring part 51. 12, 2018.
(ECAM) and procedures stated in the (2) You must use this service information ADDRESSES: For service information
applicable AFM, the AFM procedures as applicable to do the actions required by identified in this final rule, contact
prevail. this AD, unless this AD specifies otherwise. International Aero Engines (IAE), 400
amozie on DSK3GDR082PROD with RULES
(i) Airbus A350 Temporary Revision (TR)
(h) Other FAA AD Provisions Main Street, East Hartford, CT, 06118;
113, Issue 1.0, dated July 27, 2018.
The following provisions also apply to this (ii) Reserved. phone: 800–565–0140; email: help24@
AD: (3) For service information identified in pw.utc.com; internet: http://
(1) Alternative Methods of Compliance this AD, contact Airbus SAS, Airworthiness fleetcare.pw.utc.com. You may view this
(AMOCs): The Manager, International Office—EAL, Rond-Point Emile Dewoitine service information at the FAA, Engine
Section, Transport Standards Branch, FAA, No: 2, 31700 Blagnac Cedex, France; and Propeller Standards Branch, 1200
VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\07NOR1.SGM 07NOR1](https://thefederalregister.org/doc/83_FR_55835/page/1.svg)
![Federal Register / Vol. 83, No. 216 / Wednesday, November 7, 2018 / Rules and Regulations 55621
(4) Will not have a significant (b) Affected ADs whichever occurs later, and replace with a
economic impact, positive or negative, None. part eligible for installation:
on a substantial number of small entities (1) For PW1122G–JM, PW1124G1–JM,
(c) Applicability PW1124G–JM, PW1127G1–JM, PW1127GA–
under the criteria of the Regulatory
Flexibility Act. This AD applies to International Aero JM, and PW1127G–JM engines, remove the
Engines (IAE) PW1133G–JM, PW1133GA–JM, HPC front hub before exceeding 6,180 cycles
List of Subjects in 14 CFR Part 39 PW1130G–JM, PW1127G–JM, PW1127GA– since new (CSN) or within five years since
Air transportation, Aircraft, Aviation JM, PW1127G1–JM, PW1124G–JM, the ship date listed in Table 1 to paragraph
safety, Incorporation by reference, PW1124G1–JM, and PW1122G–JM turbofan (g) of this AD, whichever occurs first.
Safety. engines with a high-pressure compressor (2) For PW1130G–JM, PW1133GA–JM, and
(HPC) front hub, part number (P/N) 30G2401,
PW1133G–JM engines, remove the HPC front
Adoption of the Amendment installed.
hub before exceeding 4,440 CSN or within
Accordingly, under the authority (d) Subject four years since the ship date listed in Table
delegated to me by the Administrator, Joint Aircraft System Component (JASC) 1 to paragraph (g) of this AD, whichever
the FAA amends 14 CFR part 39 as Code 7230, Turbine Engine Compressor occurs first.
follows: Section. (3) For engines operating as a mix of
models listed in paragraphs (g)(1) and (2) of
PART 39—AIRWORTHINESS (e) Unsafe Condition
this AD, remove the HPC front hub using a
DIRECTIVES This AD was prompted by corrosion found CSN calculated by an approved FAA method
on the HPC front hub, P/N 30G2401, or within four years since the ship date listed
■ 1. The authority citation for part 39 installed. We are issuing this AD to prevent in Table 1 to paragraph (g) of this AD,
continues to read as follows: cracking and failure of the HPC front hub. whichever occurs first. You may find
Authority: 49 U.S.C. 106(g), 40113, 44701. The unsafe condition, if not addressed, could
guidance for an approved FAA method of
result in uncontained HPC front hub release,
mixed model CSN calculation in Section
§ 39.13 [Amended] damage to the engine, and damage to the
airplane. PW1000G–C–05–10–00–02A–288A–D of the
■ 2. The FAA amends § 39.13 by adding PW1100G–JM Series Airworthiness
the following new airworthiness (f) Compliance Limitations Manual, P/N 5316993, dated
directive (AD): Comply with this AD within the September 30, 2015.
AD 2018–22–02 International Aero compliance times specified, unless already (4) For any HPC front hub, P/N 30G2401,
Engines: Amendment 39–19475; Docket done. whose serial number is not listed in Table 1
No. FAA–2018–0431; Product Identifier (g) Required Actions to paragraph (g) of this AD, use October 21,
2018–NE–16–AD. 2015, as the ship date.
Remove from service the HPC front hub, P/
(a) Effective Date N 30G2401, within 120 days after the
BILLING CODE 4910–13–P
This AD is effective December 12, 2018. effective date of this AD, or as follows,
amozie on DSK3GDR082PROD with RULES
VerDate Sep<11>2014 16:15 Nov 06, 2018 Jkt 247001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\07NOR1.SGM 07NOR1](https://thefederalregister.org/doc/83_FR_55835/page/3.svg)
Document Created: 2018-11-07 00:04:23
Document Modified: 2018-11-07 00:04:23
| 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 12, 2018. | |
| Contact | Kevin M. Clark, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone: 781-238-7088; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 83 FR 55619 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR