[Federal Register Volume 85, Number 165 (Tuesday, August 25, 2020)]
[Proposed Rules]
[Pages 52281-52284]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-18562]


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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]
RIN 2120-AA64


Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 75-
16-20, which applies to all Mitsubishi 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 requires repetitive inspections of the propeller 
pitch control (PPC) lever for security and proper rigging. Since the 
FAA issued AD 75-16-20, the FAA received additional reports of the PPC 
lever linkage disconnecting at the engine. In addition, Mitsubishi has 
type certificated additional airplanes that are subject to the unsafe 
condition. This proposed AD would require modification and repetitive 
inspections of the PPC lever linkage. The FAA is proposing this AD to 
address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by October 9, 
2020.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Mitsubishi 
Heavy Industries America, Inc., c/o Turbine Aircraft Services, Inc., 
4550 Jimmy Doolittle Drive, Addison, Texas 75001; telephone: (972) 248-
3108, ext. 209; fax: (972) 248-3321; internet: https://mu-2aircraft.com. 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.

Examining the AD Docket

    You may examine the AD docket on the internet 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 NPRM, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: John Turner, Aerospace Engineer, FAA, 
Fort Worth ACO Branch, 10101 Hillwood Parkway, Fort Worth, Texas 76177; 
telephone: (817) 222-4508; fax: (817) 222-5245; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2020-0781; 
Product Identifier 2018-CE-045-AD'' at the beginning of your comments. 
The most helpful comments reference a specific portion of the proposal, 
explain the reason for any recommended change, and include supporting 
data. The FAA will consider all comments received by the closing date 
and may amend this proposed AD based on those comments.
    Except for Confidential Business Information as described in the 
following paragraph and other information as described in 14 CFR 11.35, 
the FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this proposed AD.

Confidential Business Information

    Confidential Business Information (CBI) is commercial or financial 
information that is both customarily and actually treated as private by 
its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), 
CBI is exempt from public disclosure. If your comments responsive to 
this NPRM contain commercial or financial information that is 
customarily treated as private, that you actually treat as private, and 
that is relevant or responsive to this NPRM, it is important that you 
clearly designate the submitted comments as CBI. Please mark each page 
of your submission containing CBI as ``PROPIN.'' The FAA will treat 
such marked submissions as confidential under the FOIA, and they will 
not be placed in the public docket of this NPRM. Submissions containing 
CBI should be sent to John Turner, Aerospace Engineer, FAA, Fort Worth 
ACO Branch, 10101 Hillwood Parkway, Fort Worth, Texas 76177; telephone: 
(817) 222-4508; fax: (817) 222-5245; email: [email protected]. Any 
commentary that the FAA receives which is not specifically designated 
as CBI will be placed in the public docket for this rulemaking.

Discussion

    The FAA issued AD 75-16-20, Amendment 39-2294 (40 FR 31751, July 
29, 1975) (``AD 75-16-20''), for 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. AD 75-16-20 requires 
repetitively inspecting the PPC lever for security and proper rigging. 
AD 75-16-20 resulted from reports of the PPC lever linkage 
disconnecting from the engine. The FAA issued AD 75-16-

[[Page 52282]]

20 to prevent separation of the PPC lever, which could lead to the 
inability to control the propeller pitch with the power lever in the 
cockpit and subsequent loss of control of the engine power settings.

Actions Since AD 75-16-20 Was Issued

    Since the FAA issued AD 75-16-20, the FAA received reports of the 
PPC lever linkage disconnecting at the engine, which resulted in the 
inability to control the propeller pitch with the power lever in the 
cockpit. This condition, if uncorrected, could lead to loss of control 
of the engine power settings. In addition, Mitsubishi developed a 
secondary retention feature to secure the PPC. To correct this unsafe 
condition, the Japan Civil Aviation Bureau (JCAB), which is the 
aviation authority for Japan, issued JCAB AD No. TCD-8678-2016, dated 
February 5, 2016 (referred to after this as the mandatory continuing 
airworthiness information or ``the MCAI'') to correct an unsafe 
condition for certain Mitsubishi Heavy Industries, Ltd. Model MU-2B, 
MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-30, MU-2B-35, and MU-2B-
36 airplanes. The MCAI requires replacing the PPC lever bolt with the 
new bolt.
    This proposed AD would require this bolt replacement and would also 
require installing a secondary retention feature and repetitive 
inspections of the PPC lever to prevent future reoccurrence.
    Also since AD 75-16-20 was issued, Mitsubishi has type certificated 
Models MU-2B-26A, MU-2B-36A, MU-2B-40, and MU-2B-60 airplanes. These 
models have the same PPC configuration and are subject to the same 
unsafe condition. As a result, the proposed AD would add these models 
to the applicability. You may examine the MCAI in the AD docket on the 
internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2020-0781.

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 contains 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 contains 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 the ADDRESSES section.

FAA's Determination

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, the FAA 
has been notified of the unsafe condition described in the MCAI and 
service information referenced above. The FAA is proposing this AD 
because the FAA evaluated all the relevant information and determined 
the unsafe condition described previously is likely to exist or develop 
on other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain the repetitive inspection 
requirements of AD 75-16-20 and would also require installing a 
secondary retention feature and reporting certain inspection results to 
the FAA. In addition, this proposed AD would add models to the 
applicability that were not type certificated when AD 75-16-20 was 
issued.

Differences Between This Proposed AD and the MCAI

    This proposed AD would require an installation of a secondary 
retention feature in the threaded end of the PPC input shaft, 
repetitive inspections of the security of the PPC lever, and reporting 
certain inspection results to the FAA. The MCAI does not include these 
requirements.
    The applicability of the MCAI is limited to certain Mitsubishi 
airplane models and serial numbers. However, this proposed AD would 
apply to all 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 because the type design allows 
installation of the affected PCC lever linkage on other models.

Costs of Compliance

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

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

[[Page 52283]]



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

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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 (AD) 75-16-20, Amendment 39-2294 
(40 FR 31751, July 29, 1975); and
0
b. Adding the following new AD:

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

(a) Comments Due Date

    The FAA must receive comments by October 9, 2020.

(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.

[[Page 52284]]

    (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 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 on the internet 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, 
Aerospace Engineer, FAA, Fort Worth ACO Branch, 10101 Hillwood 
Parkway, Fort Worth, Texas 76177; telephone: (817) 222-4508; fax: 
(817) 222-5245; email: [email protected].
    (3) For 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; 
telephone: (972) 248-3108, ext. 209; fax: (972) 248-3321; internet: 
https://mu-2aircraft.com. 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.

    Issued on August 19, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-18562 Filed 8-24-20; 8:45 am]
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