[Federal Register Volume 63, Number 190 (Thursday, October 1, 1998)]
[Rules and Regulations]
[Pages 52583-52585]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25957]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-39-AD; Amendment 39-10807; AD 98-20-39]
RIN 2120-AA64


Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. MU-2B 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B 
series airplanes. This AD requires inspecting each forward attachment 
fitting bolt of the wing tip tanks for the correct bolt and replacing 
any incorrect bolt. This AD is the result of mandatory continuing 
airworthiness information (MCAI) issued by the airworthiness authority 
for Japan. The actions specified by this AD are intended to prevent the 
wing tip tank from separating from the airplane because of an incorrect 
bolt corroding, which could result in loss of control of the airplane.

DATES: Effective November 20, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 20, 1998.

ADDRESSES: Mitsubishi MU-2 Service Bulletin (SB) No. 225, dated 
September 29, 1995, may be obtained from Mitsubishi Heavy Industries, 
Ltd., Nagoya Aerospace Systems Works, 10, OYE-CHO, MINATO-KU, Nagoya, 
Japan; telephone: NAGOYA (611) 2141; facsimile: 4464561HISI. Mitsubishi 
MU-2 SB No. 089/57-002A, dated November 5, 1996, may be obtained from 
the Raytheon Aircraft Company, 9709 East Central, Wichita, Kansas 
67201, Attention: Manager, Publications. This information may also be 
examined at the Federal Aviation Administration (FAA), Central Region, 
Office of the Regional Counsel, Attention: Rules Docket No. 98-CE-39-
AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106; or at 
the Office of the Federal Register, 800 North Capitol Street, NW, suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. William Roberts, Aerospace 
Engineer, FAA, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California 90712; telephone: (562) 627-
5228; facsimile: (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to certain Mitsubishi 
MU-2B series airplanes was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on July 21, 1998 (63 FR 39051). 
The NPRM proposed to require inspecting each forward attachment fitting 
bolt of the wing tip tanks to determine whether any bolt incorporating 
P/N 017A-12887, P/N 017A-12887-3, P/N 017A-12887A-5, or 017A-12887-7 is 
installed, and replacing any bolt not incorporating one of these part 
numbers, with a P/N 017A-12887A-5 or P/N 017A-12887-7 bolt. The bolts 
that apply to each model and serial number airplanes are specified in 
the service bulletins referenced below. The P/N 017A-12887A-5 and P/N 
017A-12887-7 bolts are of similar design to the P/N 017A-12887 and P/N 
017A-12887-3 bolts, and are identified with the black painted letters 
``SPL''. The NPRM also proposed to require identifying any P/N 017A-
12887 or P/N 017A-12887-3 bolt with the letters ``SPL''. Accomplishment 
of the proposed actions as specified in the NPRM would be in accordance 
with Mitsubishi MU-2 Service Bulletin (SB) No. 225, dated September 29, 
1995, and Mitsubishi MU-2 SB No. 089/57-002A, dated November 5, 1996.
    The NPRM was the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for Japan.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 252 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 1 workhour per 
airplane to accomplish the inspection, and that the average labor rate 
is approximately $60 an hour. Based on these figures, the total cost 
impact of the inspection on U.S. operators is estimated to be $15,120, 
or $60 per airplane.
    Any replacements that will be required by this AD will take 
approximately 4 workhours per airplane with each bolt costing $350 (up 
to 4 to 5 bolts per airplane depending on the configuration).

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (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); 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. A copy of the final evaluation prepared for this 
action is contained in the Rules Docket. A copy of it may be obtained 
by contacting the

[[Page 52584]]

Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

98-20-39  Mitsubishi Heavy Industries, Ltd.: Amendment 39-10807; 
Docket No. 98-CE-39-AD.

    Applicability: The following airplane model and serial number 
airplanes:

------------------------------------------------------------------------
                    Models                           Serial numbers
------------------------------------------------------------------------
                       Type Certificate No. A2PC
------------------------------------------------------------------------
MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-    008 through 312, 314
 25, and MU-2B-26.                              through 320, and 322
                                                through 347.
MU-2B-30, MU-2B-35, and MU-2B-36.............  501 through 651, 653
                                                through 660, and 662
                                                through 696.
------------------------------------------------------------------------
                       Type Certificate No. A10SW
------------------------------------------------------------------------
MU-2B-25, MU-2B-26, MU-2B-26A, and MU-2B-40..  313SA, 321SA, 348SA and
                                                through 459SA.
MU-2B-35, MU-2B-36A, and MU-2B-60............  652SA, 661SA, and 697SA
                                                through 1569SA.
------------------------------------------------------------------------

    Note 1: Mitsubishi Heavy Industries, Ltd. holds both Type 
Certificate No. A2PC and Type Certificate No. A10SW for the affected 
airplanes. Raytheon manufactures, in the United States, the 
airplanes affected by Type Certificate No. A10SW under a licensing 
agreement with Mitsubishi Heavy Industries, Ltd.
    Note 2: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (e) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated in the body of this AD, unless 
already accomplished.
    To prevent the wing tip tank from separating from the airplane 
because of an incorrect bolt corroding, which could result in loss 
of control of the airplane, accomplish the following:
    (a) Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD, inspect each forward attachment fitting 
bolt (up to 4 to 5 bolts per airplane depending on the 
configuration) of the wing tip tanks to determine whether any bolt 
not incorporating part number (P/N) 017A-12887, P/N 017A-12887-3, P/
N 017A-12887A-5, or P/N 017A-12887-7, is installed. The bolts that 
apply to each model and serial number airplanes are specified in the 
service bulletins referenced below. Accomplish this inspection in 
accordance with whichever of the following is applicable:
    (1) Mitsubishi MU-2 Service Bulletin No. 225, dated September 
29, 1995, for airplanes affected by Type Certificate No. A2PC; or
    (2) Mitsubishi MU-2 Service Bulletin No. 089/57-002A, dated 
November 5, 1996, for airplanes affected by Type Certificate No. 
A10SW.
    (b) If any bolt not incorporating P/N 017A-12887, P/N 017A-
12887-3, P/N 017A-12887A-5, or P/N 017A-12887-7, is installed, prior 
to further flight, replace it with a P/N 017A-12887-5 or P/N 017A-
12887-7 bolt as applicable and as specified in the service 
information. The P/N 017A-12887-5 and P/N 017A-12887-7 bolts are of 
similar design to the P/N 017A-12887 and P/N 017A-12887-3 bolts, and 
are identified with the black painted letters ``SPL''. Accomplish 
this action in accordance with one of the service bulletins listed 
in paragraphs (a)(1) and (a)(2) of this AD, as applicable.
    (c) If any P/N 017A-12887 or P/N 017A-12887-3 bolt is installed, 
prior to further flight, identify the bolt with the letters ``SPL''. 
Accomplish this action in accordance with one of the service 
bulletins listed in paragraphs (a)(1) and (a)(2) of this AD, as 
applicable.
    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Blvd., Lakewood, California 90712. The 
request shall be forwarded through an appropriate FAA Maintenance 
Inspector, who may add comments and then send it to the Manager, Los 
Angeles ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (f) Questions or technical information related to Mitsubishi MU-
2 Service Bulletin No. 225, dated September 29, 1995, should be 
directed to Mitsubishi Heavy Industries, Ltd., Nagoya Aerospace 
Systems Works, 10, OYE-CHO, MINATO-KU, Nagoya, Japan; telephone: 
NAGOYA (611) 2141, facsimile: 4464561HISI. Questions or technical 
information related to Mitsubishi MU-2 Service Bulletin No. 089/57-
002A, dated November 5, 1996, should be directed to Raytheon 
Aircraft Company, 9709 East Central, Wichita, Kansas 67201, 
Attention: Manager, Publications. This service information may be 
examined at the FAA, Central Region, Office of the Regional Counsel, 
Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
    (g) The inspection, replacements, and modification required by 
this AD shall be done in accordance with Mitsubishi MU-2 Service 
Bulletin No. 225, dated September 29, 1995, or Mitsubishi MU-2 
Service Bulletin No. 089/57-002A, dated November 5, 1996. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Mitsubishi Heavy Industries, Ltd., 
Nagoya Aerospace Systems Works, 10, OYE-CHO, MINATO-KU, Nagoya, 
Japan or Raytheon Aircraft Company, 9709 East Central, Wichita, 
Kansas 67201. Copies may be inspected at the FAA, Central Region, 
Office of the Regional Counsel, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri, or at the Office of the Federal Register, 800 
North Capitol Street, NW, suite 700, Washington, DC.

    Note 4: The subject of this AD is addressed in Japanese AD KU-
KI-158 TCD-4310-96, dated March 25, 1996.

    (h) This amendment becomes effective on November 20, 1998.


[[Page 52585]]


    Issued in Kansas City, Missouri, on September 22, 1998.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-25957 Filed 9-30-98; 8:45 am]
BILLING CODE 4910-13-U