[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:
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Models Serial numbers
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Type Certificate No. A2PC
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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.
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Type Certificate No. A10SW
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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.
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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]
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