[Federal Register Volume 63, Number 71 (Tuesday, April 14, 1998)]
[Proposed Rules]
[Pages 18151-18153]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-9584]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-27-AD]
RIN 2120-AA64
Airworthiness Directives; Mitsubishi Heavy Industries, Ltd. MU-2B
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain Mitsubishi Heavy Industries, Ltd.
(Mitsubishi) MU-2B series airplanes. The proposed action would require
repetitively inspecting the cockpit windshield and cabin window
surfaces for damage (damage would be defined as crazing, scratches, and
cracks). If any of the windshield or window surfaces have damage that
exceeds certain limits, the proposed AD would require replacing the
windshield or window. If the damage does not exceed certain limits,
then the proposed AD would allow blending out the damage following
maintenance manual procedures. The proposed AD is the result of
mandatory continuing airworthiness information (MCAI) issued by the
airworthiness authority for Japan. The actions specified by the
proposed AD are intended to prevent cockpit windshield or cabin window
separation during flight, which could result in engine ingestion of
glass, wing skin damage, or propeller damage, and possible loss of
control of the airplane.
DATES: Comments must be received on or before May 11, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 97-CE-27-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106. Comments may be inspected at this location
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
Service information that applies to the proposed AD may be obtained
from Mitsubishi Heavy Industries, Ltd., Nagoya Aerospace Systems Works,
10. OYE-CHO, MINATO-KU, Nagoya, Japan, telephone: NAGOYA (611) 2141,
telex: 4464561HISI. This information also may be examined at the Rules
Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. William Roberts, Aerospace
Engineer, Los Angeles Aircraft Certification Office, FAA, 3960
Paramount Blvd., Lakewood, California, 90712; telephone (562) 627-5224;
facsimile (562) 627-5228.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 97-CE-27-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 97-CE-27-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
The Japanese Civil Airworthiness Bureau (JCAB), which is the
airworthiness authority for Japan, recently notified the FAA that an
unsafe condition may exist on certain Mitsubishi MU-2B series
airplanes. The JCAB reports that several Mitsubishi MU-2B series
airplanes have had windshield or window separation during flight.
Separation would be defined as shattering glass. Further analysis shows
that the separation is happening as a result of repeated cabin
pressurization cycles. These conditions, if not corrected, could result
in shattering or separation of the cockpit windshield or cabin windows
during flight, which could cause loss of control of the airplane.
Relevant Service Information
Mitsubishi has issued MU-2 Service Bulletin (SB) No. 224, dated
June 30, 1995, and MU-2 SB No. 224A, dated October 30, 1995, which
specifies procedures for repetitively inspecting and repairing or
replacing the cockpit windshield (part numbers (P/N) 010A-31450-1/-2,
P/N 010A-31451-1/-2, and P/N 010A-81874-1/-2 or an FAA-approved
equivalent part number) or cabin windows (P/N 010A-31870, P/N 010A-
31870-11, and P/N 030A-32402, or an FAA-approved equivalent part
number), depending on the extent of the scratching, crazing, or
cracking. If the scratching, crazing, or cracking is within the
acceptable limits called out in Table 1 of the service bulletin, the
procedure for repairing or blending out any damage is found in Chapter
3 of the Mitsubishi maintenance manual.
The JCAB classified these service bulletins as mandatory and issued
AD No. TCD-4311-95, dated November 15, 1995, in order to assure the
continued airworthiness of these airplanes in Japan. The Japanese AD
confirms that the cause of glass shattering is the repeated
pressurization of the airplane cabin, and refers the operators to the
Mitsubishi service bulletins for inspection and repair instructions,
but the AD did not cite the incidents of shattered windows on the MU-2B
series airplanes during flight as the reason for the issuance of the
JCAB AD.
The FAA's Determination
These Mitsubishi MU-2B series airplanes are manufactured in Japan
and are type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the JCAB has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the JCAB, reviewed all available information including the
service information referenced above, and determined that AD action is
necessary for products of
[[Page 18152]]
this type design that are certificated for operation in the United
States.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Mitsubishi MU-2B series airplanes of the same
type design registered in the United States, the FAA is proposing AD
action. The proposed AD would require repetitively inspecting the
affected cockpit windshields and cabin windows for damage and repairing
or replacing the affected glass, depending on the extent of the damage.
Accomplishment of the proposed inspection, and repair or replacement
would be in accordance with Mitsubishi MU-2 Service Bulletin (SB) No.
224, dated June 30, 1995, and MU-2 SB No. 224A, dated October 30, 1995.
Cost Impact
The FAA estimates that 200 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 8
workhours to accomplish the proposed inspection, and that the average
labor rate is approximately $60 an hour. If a replacement window is
needed, it would take approximately 16 workhours to accomplish the
replacement with the average labor rate of $60 per hour. Parts are
provided at no cost by the manufacturer. Based on these figures, the
total cost for the inspection would be $480 per airplane or $96,000 for
the entire U.S. registered fleet. If a replacement is needed, the total
cost impact of the proposed AD on U.S. operators is estimated to be
$192,000 or $960 per airplane.
Regulatory Impact
The regulations proposed herein would 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
proposal would 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) if promulgated,
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 draft regulatory evaluation
prepared for this action has been placed in the Rules Docket. A copy of
it may be obtained by contacting the Rules Docket at the location
provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Mitsubishi Heavy Industries, Ltd. (Mitsubishi): Docket No. 97-CE-27-
AD.
Applicability: Models MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-
2B-25, MU-2B-26 airplanes (serial numbers (S/N) 008 through 312, 314
through 320, and 322 through 347), and MU-2B-30, MU-2B-35, MU-2B-36
airplanes (S/N 501 through 651, 653 through 660, and 662 through
696), certificated in any category, that are equipped with the
following part numbered windshields and cabin windows:
010A-31450-1/-2....................... Windshield (LH/RH).
010A-31451-1/-2....................... Cockpit side window (LH/RH).
010A-81874-1/-2....................... Cockpit side window (LH/RH).
010A-31870............................ Cabin Window.
010A-31870-11......................... Cabin Window (at door).
030A-32402............................ Long body-small cabin window.
Note 1: 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 within the next 100 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished, and thereafter at intervals not to exceed 100 hours
TIS from the last inspection, repair or replacement.
To prevent cockpit windshield or cabin window separation
(shattering) during flight, which could result in engine ingestion
of glass, wing skin damage, or propeller damage, and possible loss
of control of the airplane, accomplish the following:
(a) Inspect the cockpit windshields and cabin windows for
scratching, crazing, and cracking in accordance with Part I and
Table 1. ``Damage and Definitions'' of the Instructions section in
Mitsubishi MU-2 Service Bulletin (SB) No. 224, dated June 30, 1995,
and Mitsubishi MU-2 SB No. 224A, dated October 30, 1995.
(b) If any of the windshields or windows listed in the
applicability section of this AD are damaged beyond the limits
according to Part I, paragraph 3. ``Acceptable Limits for Damage''
of the Instructions section, prior to further flight, replace the
window or windshield in accordance with the Part II ``Windshield/
Window Glass Replacement'' section of the Mitsubishi MU-2 SB No.
224, dated June 30, 1995, Mitsubishi MU-2 SB No. 224A, dated October
30, 1995, and Chapter 3 of the applicable Mitsubishi Maintenance
Manual.
(c) Prior to further flight, repair any damaged windshield or
window that is within the limits (referenced in Table 2 of
Mitsubishi MU-2 SB No. 224, dated June 30, 1995) in accordance with
Chapter 3 of the applicable Mitsubishi Maintenance Manual.
(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
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Los Angeles Aircraft
Certification Office, FAA, 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 Aircraft Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles Aircraft Certification Office.
(f) All persons affected by this directive may obtain copies of
the documents referred to herein upon request to Mitsubishi Heavy
Industries, Ltd., Nagoya Aerospace Systems Works, 10. OYE-CHO,
MINATO-KU, Nagoya, Japan; or may examine these documents at the FAA,
Central Region, Office of the Regional Counsel, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106.
Note 3: The subject of this AD is addressed in Japanese AD No.
TCD-4311-95, dated November 15, 1995.
[[Page 18153]]
Issued in Kansas City, Missouri, on April 3, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-9584 Filed 4-13-98; 8:45 am]
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