AD 2020-26-14

The FAA is superseding Airworthiness Directive (AD) 75-16-20, which applied to all Mitsubishi Heavy Industries, Ltd., Model MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-30, MU-2B-35, and MU-2B-36 airplanes. AD 75-16-20 required repetitive inspections of the propeller pitch control (PPC) lever for security and proper rigging. This AD requires \n\n((Page 85507)) \n\nmodification and repetitive inspections of the PPC lever linkage. The FAA is issuing this AD to address the unsafe condition on these products.

Final rule.

The Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by: 0 a. Removing Airworthiness Directive 75-16-20, Amendment 39-2294 (40 FR 31751, July 29, 1975); and 0 b. Adding the following new airworthiness directive: \n\n2020-26-14 Mitsubishi Heavy Industries, Ltd.: Amendment 39-21369; Docket No. FAA-2020-0781; Product Identifier 2018-CE-045-AD. \n\n(a) Effective Date \n\n\n\tThis airworthiness directive (AD) is effective February 2, 2021. \n\n(b) Affected ADs \n\n\n\tThis AD replaces AD 75-16-20, Amendment 39-2294 (40 FR 31751, July 29, \n\t1975) (AD 75-16-20). \n\n(c) Applicability \n\n\n\tThis AD applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) Models MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, MU-2B- 40, and MU-2B-60 airplanes, certificated in any category. \n\n(d) Subject \n\n\n\tAir Transport Association (ATA) of America Code 61: Propellers. \n\n(e) Reason \n\n\n\tThis AD was prompted by propeller pitch control (PPC) lever linkages disconnecting at the engine. The FAA is issuing this AD to address the PPC lever linkage from disconnecting at the engine, which could lead to the inability to control the propeller pitch with the power lever in the cockpit and consequent loss of control of the engine power settings. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Modification \n\n\n\t(1) For all airplanes except Model MU-2B and MU-2B-10 airplanes: Within 100 hours time-in-service (TIS) after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, modify the PPC lever linkage asspecified in paragraphs (g)(1)(i) through (iii) of this AD, as applicable. \n\t(i) Replace the PPC lever clamping bolt in accordance with the Accomplishment Instructions, section 2, of Mitsubishi MU-2 Service Bulletin No. 106/76-004, dated February 24, 2016, or Mitsubishi MU-2 Service Bulletin No. 244, dated December 25, 2015, as applicable to your model airplane. \n\t(ii) For airplanes without a threaded hole in the splined end of the shouldered shaft of the PPC assembly, incorporate a threaded hole in accordance with the Accomplishment Instructions, paragraph 3.C.(3)(d)2, of Honeywell International Inc. Service Bulletin TPE331-72-2190, Revision 0, dated December 21, 2011. \n\t(iii) Install a secondary retention feature in the threaded end of the PPC input shaft in accordance with the Accomplishment Instructions, section 2, of Mitsubishi MU-2 Service Recommendation No. 049/76-002, dated June 29, 2018, or Mitsubishi MU-2 Service Recommendation No. 080, dated June 29, 2018, as applicableto your model airplane. \n\t(2) For Model MU-2B and MU-2B-10 airplanes: Within 100 hours TIS after the effective date of this AD or within 12 months after the effective date of this AD, whichever \n\n((Page 85509)) \n\noccurs first, replace the PPC lever clamping bolt and install a secondary retention feature in the threaded end of the PPC input shaft using a method approved by the Manager of the Fort Worth ACO Branch, FAA. The Manager's approval letter must specifically refer to this AD. \n\n(h) Repetitive Inspections and Reporting \n\n\n\tWithin 100 hours TIS after replacing the bolt and installing a secondary retention feature as required by paragraph (g) of this AD and thereafter at intervals not to exceed 100 hours TIS, inspect the security of the PPC lever by pulling the PPC lever upward by hand to ensure it does not detach from the PPC input shaft. If the PPC lever detaches, do the following. \n\t(1) Before further flight, install the PPC lever using a method approved by the Manager of the Fort Worth ACO Branch, FAA. The Manager's approval letter must specifically refer to this AD. \n\t(2) Within 30 days after the PPC lever detachment or within 30 days after the effective date of this AD, whichever occurs later, report the results of the inspection, including airplane model and serial number, to the FAA representative identified in paragraph (l)(2) of this AD. \n\n(i) Special Flight Permit \n\n\n\t(1) Special flight permits may be issued for the purpose of operating the airplane to a location where the requirements of paragraph (g) of this AD can be performed with the following limitations: Flights must not carry passengers, must operate in daytime visual meteorological conditions only, and must not operate in areas of known turbulence. \n\t(2) Special flight permits may be issued for the purpose of operating the airplane to a location where the requirements of paragraph (h) of this AD may be performed without limitations. \n\n(j) Paperwork Reduction Act Burden Statement \n\n\n\tA federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. All responses to this collection of information are mandatory as required by this AD; the nature and extent of confidentiality to be provided, if any. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524. \n\n(k) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Fort Worth 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 Fort Worth ACO Branch, send it to the attention of the person identified in paragraph (l)(2) of this AD. \n\t(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. \n\n(l) Related Information \n\n\n\t(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Japan Civil Aviation Bureau (JCAB) AD No. TCD-8678-2016, dated February 5, 2016, for related information. This MCAI may be found in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-0781. \n\t(2) For more information about this AD, contact John Turner, Aviation Safety Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 76177; phone: (817) 222-4508; fax: (817) 222-5245; email: johh.r.turner@faa.gov. \n\n(m) Material Incorporated by Reference \n\n\n\t(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. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. \n\t(i) Honeywell International Inc. Service Bulletin TPE331-72- 2190, Revision 0, dated December 21, 2011. \n\t(ii) Mitsubishi MU-2 Service Bulletin No. 244, dated December 25, 2015. \n\t(iii) Mitsubishi MU-2 Service Bulletin No. 106/76-004, dated February 24, 2016. \n\t(iv) Mitsubishi MU-2 Service Recommendation No. 049/76-002, dated June 29, 2018. \n\t(v) Mitsubishi MU-2 Service Recommendation No. 080, dated June 29, 2018. \n\t(3) For Mitsubishi service information identified in this AD, contact Mitsubishi Heavy Industries America, Inc., c/o Turbine Aircraft Services, Inc., 4550 Jimmy Doolittle Drive, Addison, Texas 75001; phone: (972) 248-3108, ext. 209; fax: (972) 248-3321; website: https://mu-2aircraft.com. \n\t(4) For Honeywell service information identified in this AD, contact Honeywell International Inc., 111 S 34th Street, Phoenix, Arizona 85034-2802; phone: 855-808-6500; email: AeroTechSupport@honeywell.com; website: https://aerospace.honeywell.com/en/services/maintenance-and-monitoring. \n\t(5) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. \n\t(6) 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, email: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\tIssued on December 11, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2020-28855 Filed 12-28-20; 8:45 am) BILLING CODE 4910-13-P

Background \n\n\n\tThe FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 75-16-20, Amendment 39-2294 (40 FR 31751, July 29, 1975) (AD 75-16-20). AD 75-16-20 applied to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) Models MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-30, MU-2B-35, and MU-2B-36 airplanes. The NPRM published in the Federal Register on August 25, 2020 (85 FR 52281). The NPRM was prompted by reports of the PPC lever linkages disconnecting at the engine and Mitsubishi developing a secondary retention feature to secure the PPC. The NPRM was also prompted by Mitsubishi type certificating additional airplanes that are subject to the unsafe condition. In the NPRM, the FAA proposed to require installation of the secondary retention feature, repetitive inspections of the PPC lever linkage, and reporting inspection results to the FAA. \n\nComments \n\n\n\tThe FAA received no comments on the NPRM or on the determination of the costs. \n\nConclusion \n\n\n\tThe FAA reviewed the relevant data and determined that air safety requires adoption of the AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. \n\nRelated Service Information Under 1 CFR Part 51 \n\n\n\tMitsubishi has issued MU-2 Service Recommendation No. 049/76-002, dated June 29, 2018, and MU-2 Service Recommendation No. 080, dated June 29, 2018. This service information specifies procedures for installing a PPC lever secondary retention feature to secure the PPC lever. These documents are distinct since they apply to different airplane models and configurations. \n\tMitsubishi has also issued MU-2 Service Bulletin No. 106/76-004, dated February 24, 2016, and MU-2 Service Bulletin No. 244, dated December 25, 2015. This service information specifies procedures for replacing the PPC lever clamping bolt. These documents are distinct since they apply to different airplane models and configurations. \n\tHoneywell International Inc. has issued Service Bulletin TPE331-72- 2190, Revision 0, dated December 21, 2011. The procedures in this service information include instructions for incorporating a threaded hole in the splined end of the shouldered shaft of the PPC assembly and re-identifying the shouldered shaft part number. The threaded hole is used to accommodate a secondary retention method to secure the PPC lever. \n\tThis 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 ADDRESSES. \n\nCosts of Compliance \n\n\n\tThe FAA estimates that this AD affects 260 airplanes of U.S. registry. \n\tThe FAA estimates the following costs to comply with this AD. The average labor rate is $85 per work hour. \n\n\n\tEstimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- \n\tParts \n\tAction Labor cost cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Modification........................... 2 work-hours x $85 per hour = $2 $172.................................. $44,720. \n\t$170. Repetitive inspections................. 1 work-hour x $85 per hour = 0 $85 per inspection cycle.............. $22,100 per inspection \n\t$85 per inspection cycle. cycle. -------------------------------------------------------------------------------------------------------------------------------------------------------- \n\n\n\tThe FAA estimates the following costs to do any necessary on- condition actions for the incorporation of the threaded hole and reporting requirement. The FAA has no way of determining the number of aircraft that might need these on-condition actions: \n\n\n\tOn-Condition Costs ---------------------------------------------------------------------------------------------------------------- \n\tCost per \n\tAction Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Incorporation of threaded hole......... 4 work-hours x $85 per hour = $340..... $1,000 $1,340 \n\n((Page 85508)) \n\n\n\nReporting.............................. 1 work-hour x $85 per hour = $85....... 0 85 ---------------------------------------------------------------------------------------------------------------- \n\n\n\tIf the PPC lever detaches, the necessary corrective actions could vary significantly from airplane to airplane. The FAA has received no definitive data that would enable estimating the cost to install the PPC lever on each airplane or the number of airplanes that may require this action. \n\nPaperwork Reduction Act \n\n\n\tA federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524. \n\nAuthority for This Rulemaking \n\n\n\tTitle 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. \n\tThe FAA is 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 ofthat authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. \n\nRegulatory Findings \n\n\n\tThe FAA has 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. \n\tFor the reasons discussed above, I certify that this AD: \n\t(1) Is not a ''significant regulatory action'' under Executive Order 12866, \n\t(2) Will not affect intrastate aviation in Alaska, and \n\t(3) 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. \n\nList of Subjects in 14 CFR Part 39 \n\n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.