[Federal Register Volume 72, Number 63 (Tuesday, April 3, 2007)]
[Proposed Rules]
[Pages 15850-15852]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-6121]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 72, No. 63 / Tuesday, April 3, 2007 / 
Proposed Rules  

[[Page 15850]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27191; Directorate Identifier 2007-CE-007-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directives (AD) 93-07-11 
and AD 94-04-16, which apply to certain Mitsubishi Heavy Industries MU-
2B Series airplanes. AD 93-07-11 and AD 94-04-16 currently require you 
to reduce the maximum deflection of the elevator nose-down trim to a 1-
degree to 3-degree range. When the above AD actions were issued, there 
was no associated elevator trim indicator change. Without such change, 
the trim reaches the maximum nose-down limit and the indicator still 
shows additional nose-down trim available. In attempting to force 
additional nose-down trim, pilots have manually jammed the trim system 
preventing subsequent electric trim changes until the pilot manually 
freed the trim wheel. Consequently, this proposed AD would retain the 
actions from AD 93-07-11 and AD 94-04-16 and add the action of 
modifying the elevator trim indicator scale dial to be consistent with 
the reduced elevator trim capability. We are proposing this AD to 
prevent the above scenarios from occurring with consequent loss of 
control.

DATES: We must receive comments on this proposed AD by June 4, 2007.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    For service information identified in this proposed AD, contact 
Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 
800, Addison, Texas 75001; telephone: 972-934-5480; facsimile: 972-934-
5488.

FOR FURTHER INFORMATION CONTACT: Werner G. Koch, Aerospace Engineer, 
Fort Worth Airplane Certification Office, ASW-150, Rotorcraft 
Directorate, FAA, 2601 Meacham Boulevard, Fort Worth, Texas 76137-4298; 
telephone: (817) 222-5133; fax: (817) 222-5960.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2007-27191; Directorate Identifier 2007-CE-007-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    Several incidents caused by excessive control wheel force on 
Mitsubishi Heavy Industries MU-2B series airplanes caused us to issue 
AD 93-07-11, Amendment 39-8543 and AD 94-04-16, Amendment 39-8836 (59 
FR 8520, February 23, 1994). AD 93-07-11 and AD 94-04-16 currently 
require you to reduce the maximum deflection of the elevator nose-down 
trim to a 1-degree to 3-degree range on certain Mitsubishi Heavy 
Industries MU-2B series airplanes.
    When the above AD actions were issued, there was no associated 
elevator trim indicator change. Consequently, when the trim reaches the 
maximum nose-down limit, the indicator still shows additional nose-down 
trim available. This condition may result in the pilot thinking that 
more nose-down trim is available beyond the mechanical stop. In 
attempting to force additional nose-down trim beyond the mechanical 
stop, pilots have manually jammed the trim system preventing subsequent 
electric trim changes until the pilot manually freed the trim wheel. 
This condition, if not corrected, could result in loss of control.

Relevant Service Information

    The following service information was included in AD 93-07-11 and 
AD 94-04-16 and will remain in effect for this AD:
     Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 
079/27-010, dated August 28, 1992; and
     Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 
216, dated September 11, 1992.
    The above service information describes procedures for reducing the 
maximum deflection of the elevator nose-down trim to a 1-degree to 3-
degree range.
    We have reviewed the following service information for this AD:
     Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 
091/27-011, dated August 6, 1998; and
     Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 
228, dated July 13, 1998.
    The above service information describes procedures for modifying 
the elevator trim indicator scale dial to be consistent with the 
elevator trim capability.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined that without the elevator trim indicator scale dial 
modifications

[[Page 15851]]

the unsafe condition described previously is likely to exist or develop 
on other products of the same type design. This proposed AD would 
supersede AD 93-07-11 and AD 94-04-16 with a new AD that would retain 
the actions from AD 93-07-11 and AD 94-04-16 and add the action of 
modifying the elevator trim indicator scale dial to be consistent with 
the elevator trim capability. This proposed AD would require you to use 
the service information described previously to perform these actions.

Costs of Compliance

    We estimate that this proposed AD would affect 400 airplanes in the 
U.S. registry.

Costs Retained From AD 93-07-11 and AD 94-04-16

    We estimate the following costs to do the proposed modification of 
the elevator nose-down trim:

----------------------------------------------------------------------------------------------------------------
                                                                                 Total cost per   Total cost on
                          Labor cost                              Parts cost        airplane      U.S. operators
----------------------------------------------------------------------------------------------------------------
6 work-hours x $80 per hour = $480...........................            $300             $780         $312,000
----------------------------------------------------------------------------------------------------------------

Additional Costs for This AD

    We estimate the following costs to do the proposed modification of 
the elevator trim indicator scale dial:

----------------------------------------------------------------------------------------------------------------
                                                                                 Total cost per   Total cost on
                          Labor cost                              Parts cost        airplane      U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80.............................             N/A              $80          $32,000
----------------------------------------------------------------------------------------------------------------

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.
    We are 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

    We have 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 that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at http://dms.dot.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5227) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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

    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 removing Airworthiness Directives 
(ADs) 93-07-11, Amendment 39-8543 and 94-04-16, Amendment 39-8836 (59 
FR 8520, February 23, 1994), and adding the following new AD:

Mitsubishi Heavy Industries: Docket No. FAA-2007-27191; Directorate 
Identifier 2007-CE-007-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by June 4, 2007.

Affected ADs

    (b) This AD supersedes AD 93-07-11, Amendment 39-8543 and AD 94-
04-16, Amendment 39-8836.

Applicability

    (c) This AD applies to the following airplane models and serial 
numbers that are certificated in any category:
    (1) Category 1 Airplanes:

[[Page 15852]]



------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
(i) MU-2B, MU-2B-10, MU-2B-15, MU-2B-    008 through 347 (except 313 and
 20, MU-2B-25, and MU-2B-26.              321).
(ii) MU-2B-30, MU-2B-35, and MU-2B-36..  501 through 696 (except 652 and
                                          661).
------------------------------------------------------------------------

    (2) Category 2 Airplanes:

------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
(i) MU-2B-25, MU-2B-26, MU-2B-26A, and   313SA, 321SA, 348SA through
 MU-2B-40.                                459SA.
(ii) MU-2B-35, MU-2B-36A, and MU-2B-60.  652SA, 661SA and 697SA through
                                          1569SA.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from several incidents caused by excessive 
control wheel force. We are issuing this AD to retain the actions of 
AD 93-07-11 and AD 94-04-16 to prevent excessive control wheel force 
caused by extreme elevator nose-down trim deflection. We are also 
issuing this AD to modify the elevator trim indicator scale dial to 
be consistent with the reduced elevator trim capability. 
Inconsistencies between the elevator indicator scale dial and the 
elevator trim mechanical stop may result in the pilot thinking that 
more nose-down trim is available beyond the mechanical stop. 
Attempting to force additional nose-down trim beyond the mechanical 
stop may jam the trim system, preventing subsequent electric trim 
changes until the pilot manually frees the trim wheel. These 
conditions may result in loss of control of the airplane.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Reduce the maximum        (i) For Category 1    (A) For Category 1
 deflection of the elevator    airplanes: Within     airplanes: Follow
 nose-down trim to a 1-        100 hours time-in-    Mitsubishi Heavy
 degree to 3-degree range.     service (TIS) after   Industries, Ltd.,
                               April 11, 1994 (the   Service Bulletin
                               effective date of     No. 216, dated
                               AD 94-04-16).         September 11, 1992.
                              (ii) For Category 2   (B) For Category 2
                               airplanes: Within     airplanes: Follow
                               100 hours TIS after   Mitsubishi Heavy
                               June 1, 1993 (the     Industries, Ltd.,
                               effective date of     Service Bulletin
                               AD 93-07-11).         No. 079/27-010,
                                                     dated August 28,
                                                     1992.
(2) Modify the elevator trim  Within 100 hours TIS  (i) For Category 1
 indicator scale dial..        after the effective   airplanes: Follow
                               date of this AD.      Mitsubishi Heavy
                                                     Industries, Ltd.,
                                                     Service Bulletin
                                                     No. 228, dated July
                                                     13, 1998.
                                                    (ii) For Category 2
                                                     airplanes: Follow
                                                     Mitsubishi Heavy
                                                     Industries, Ltd.,
                                                     Service Bulletin
                                                     No. 091/27-011,
                                                     dated August 6,
                                                     1998.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Fort Worth Airplane Certification Office (ACO), 
FAA, ATTN: Werner G. Koch, Aerospace Engineer, Fort Worth ACO, ASW-
150, Rotorcraft Directorate, FAA, 2601 Meacham Boulevard, Fort 
Worth, Texas 76137-4298; telephone: (817) 222-5133; fax: (817) 222-
5960, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Before using any 
approved AMOC on any airplane to which the AMOC applies, notify your 
appropriate principal inspector (PI) in the FAA Flight Standards 
District Office (FSDO), or lacking a PI, your local FSDO.
    (g) AMOCs approved for AD 93-07-11, Amendment 39-8543 and AD 94-
04-16, Amendment 39-8836 are approved for this AD.

Related Information

    (h) To get copies of the service information referenced in this 
AD, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport 
Parkway, Suite 800, Addison, Texas 75001; telephone: 972-934-5480; 
facsimile: 972-934-5488. To view the AD docket, go to the Docket 
Management Facility; U.S. Department of Transportation, 400 Seventh 
Street, SW., Nassif Building, Room PL-401, Washington, DC, or on the 
Internet at http://dms.dot.gov. The docket number is Docket No. FAA-
2007-27191; Directorate Identifier 2007-CE-007-AD.

    Issued in Kansas City, Missouri, on March 27, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-6121 Filed 4-2-07; 8:45 am]
BILLING CODE 4910-13-P