[Federal Register Volume 85, Number 249 (Tuesday, December 29, 2020)]
[Rules and Regulations]
[Pages 85506-85509]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-28855]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0781; Product Identifier 2018-CE-045-AD; Amendment 
39-21369; AD 2020-26-14]
RIN 2120-AA64


Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: 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

[[Page 85507]]

modification and repetitive inspections of the PPC lever linkage. The 
FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective February 2, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 2, 
2021.

ADDRESSES: For Mitsubishi service information identified in this final 
rule, 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. For Honeywell service information identified 
in this final AD, contact Honeywell International Inc., 111 S 34th 
Street, Phoenix, Arizona 85034-2802; phone: 855-808-6500; email: 
<a href="/cdn-cgi/l/email-protection#8dcce8ffe2d9e8eee5def8fdfde2fff9cde5e2e3e8f4fae8e1e1a3eee2e0"><span class="__cf_email__" data-cfemail="17567265784372747f44626767786563577f7879726e60727b7b3974787a">[email protected]</span></a>; website: https://aerospace.honeywell.com/en/services/maintenance-and-monitoring. 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. It is also available at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0781.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0781; 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, any 
comments received, and other information. The address for Docket 
Operations 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: 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: 
<a href="/cdn-cgi/l/email-protection#412b2e29296f336f3534332f2433012720206f262e37"><span class="__cf_email__" data-cfemail="442e2b2c2c6a366a3031362a2136042225256a232b32">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Background

    The 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.

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    The 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.

Related Service Information Under 1 CFR Part 51

    Mitsubishi 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.
    Mitsubishi 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.
    Honeywell 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.
    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 ADDRESSES.

Costs of Compliance

    The FAA estimates that this AD affects 260 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD. The 
average labor rate is $85 per work hour.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                           Parts
                 Action                            Labor cost               cost               Cost per product                Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification...........................  2 work-hours x $85 per hour =          $2  $172..................................  $44,720.
                                          $170.
Repetitive inspections.................  1 work-hour x $85 per hour =            0  $85 per inspection cycle..............  $22,100 per inspection
                                          $85 per inspection cycle.                                                          cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    The 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:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                 Action                                 Labor cost                  Parts cost        product
----------------------------------------------------------------------------------------------------------------
Incorporation of threaded hole.........  4 work-hours x $85 per hour = $340.....          $1,000          $1,340

[[Page 85508]]

 
Reporting..............................  1 work-hour x $85 per hour = $85.......               0              85
----------------------------------------------------------------------------------------------------------------

    If 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.

Paperwork Reduction Act

    A 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.

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.
    The 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 of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    The 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.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

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:
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:

2020-26-14 Mitsubishi Heavy Industries, Ltd.: Amendment 39-21369; 
Docket No. FAA-2020-0781; Product Identifier 2018-CE-045-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective February 2, 2021.

(b) Affected ADs

    This AD replaces AD 75-16-20, Amendment 39-2294 (40 FR 31751, 
July 29,
    1975) (AD 75-16-20).

(c) Applicability

    This 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.

(d) Subject

    Air Transport Association (ATA) of America Code 61: Propellers.

(e) Reason

    This 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.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Modification

    (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 as specified in 
paragraphs (g)(1)(i) through (iii) of this AD, as applicable.
    (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.
    (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.
    (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 applicable to your 
model airplane.
    (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

[[Page 85509]]

occurs 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.

(h) Repetitive Inspections and Reporting

    Within 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.
    (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.
    (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.

(i) Special Flight Permit

    (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.
    (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.

(j) Paperwork Reduction Act Burden Statement

    A 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.

(k) Alternative Methods of Compliance (AMOCs)

    (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.
    (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.

(l) Related Information

    (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.
    (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: <a href="/cdn-cgi/l/email-protection#a9c3c6c1c187db87dddcdbc7ccdbe9cfc8c887cec6df"><span class="__cf_email__" data-cfemail="aac0c5c2c284d884dedfd8c4cfd8eacccbcb84cdc5dc">[email protected]</span></a>.

(m) 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.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Honeywell International Inc. Service Bulletin TPE331-72-
2190, Revision 0, dated December 21, 2011.
    (ii) Mitsubishi MU-2 Service Bulletin No. 244, dated December 
25, 2015.
    (iii) Mitsubishi MU-2 Service Bulletin No. 106/76-004, dated 
February 24, 2016.
    (iv) Mitsubishi MU-2 Service Recommendation No. 049/76-002, 
dated June 29, 2018.
    (v) Mitsubishi MU-2 Service Recommendation No. 080, dated June 
29, 2018.
    (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.
    (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: 
<a href="/cdn-cgi/l/email-protection#76371304192213151e25030606190402361e1918130f01131a1a5815191b"><span class="__cf_email__" data-cfemail="d091b5a2bf84b5b3b883a5a0a0bfa2a490b8bfbeb5a9a7b5bcbcfeb3bfbd">[email protected]</span></a>; website: https://aerospace.honeywell.com/en/services/maintenance-and-monitoring.
    (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.
    (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: <a href="/cdn-cgi/l/email-protection#b3d5d6d7c1d6d49ddfd6d4d2dff3ddd2c1d29dd4dcc5"><span class="__cf_email__" data-cfemail="d2b4b7b6a0b7b5fcbeb7b5b3be92bcb3a0b3fcb5bda4">[email protected]</span></a>, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued 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


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