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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 al-
    ready 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 Accomplish-
    ment Instructions, section 2,  of Mitsubishi MU-2 Service Bulletin No.
    106/76-004, dated February 24, 2016, or Mitsubishi MU-2 Service Bulle-
    tin No. 244, dated December 25, 2015, as applicable to your model air-
    plane.

(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  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 Managerís approval letter must specifically
    refer to this AD.

(h) REPETITIVE INSPECTIONS AND REPORTING

    Within 100 hours TIS after replacing the bolt and installing a second-
    ary 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  Managerís
    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 re-
    quired 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 in-
    spector, 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: johh.r.turner@faa.gov.

(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 Mit-
    subishi 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: AeroTechSupport@honeywell.com;
    website:  https://aerospace.honeywell.com/en/services/maintenance-and-
    monitoring.

(5) You may view this service information at the FAA,  Airworthiness Prod-
    ucts 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 refer-
    ence 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.

Issued on December 11, 2020.  Lance T. Gant,  Director,  Compliance & Air-
worthiness Division, Aircraft Certification Service.

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: johh.r.turner@
faa.gov.
PREAMBLE 

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.

-----------------------------------------------------------------------

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 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:
AeroTechSupport@honeywell.com; 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:
johh.r.turner@faa.gov.

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

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

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

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]

2. The FAA amends Sec. 39.13 by:

a. Removing Airworthiness Directive 75-16-20, Amendment 39-2294 (40 FR
31751, July 29, 1975); and

b. Adding the following new airworthiness directive: