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

[Federal Register Volume 72, Number 161 (Tuesday, August 21, 2007)]
[Rules and Regulations]
[Pages 46542-46545]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-16288]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27191; Directorate Identifier 2007-CE-007-AD; 
Amendment 39-15167; AD 2007-17-09]
RIN 2120-AA64


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

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) to 
supersede 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 AD retains the actions from AD 93-07-11 and AD 94-
04-16 and adds the action of modifying the elevator trim indicator 
scale dial to be consistent with the reduced elevator trim capability. 
We are issuing this AD to prevent the above scenarios from occurring 
with consequent loss of control.

DATES: This AD becomes effective on September 25, 2007.
    On September 25, 2007, the Director of the Federal Register 
approved the incorporation by reference of Mitsubishi

[[Page 46543]]

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 listed in this AD.
    As of June 1, 1993, the Director of the Federal Register approved 
the incorporation by reference of Mitsubishi Heavy Industries, Ltd., 
Service Bulletin No. 079/27-010, dated August 28, 1992, listed in this 
AD.
    As of April 11, 1994, the Director of the Federal Register approved 
the incorporation by reference of Mitsubishi Heavy Industries, Ltd., 
Service Bulletin No. 216, dated September 11, 1992, listed in this AD.

ADDRESSES: For service information identified in this AD, contact 
Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 
800, Addison, Texas 75001; telephone: 972-934-5480; fax: 972-934-5488.
    To view the AD docket, go to U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at 
http://dms.dot.gov. The docket number is FAA-2007-27191; Directorate 
Identifier 2007-CE-007-AD.

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: 

Discussion

    On March 27, 2007, we issued 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 Heavy Industries MU-2B series 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on April 3, 2007 (72 FR 15850). 
The NPRM proposed to supersede AD 93-07-11 and AD 94-04-16, retain the 
actions of reducing the maximum deflection of the elevator nose-down 
trim to a 1-degree to 3-degree range 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.

Comments

    We provided the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and FAA's response to each comment:

Comment Issue No. 1: Increased Trim Down Limit

    Salomon R. Dionicio suggests increasing the trim down limit, 
because under certain conditions some pilots may need more down trim. 
The commenter is also concerned about the needle bending or jumping and 
the cable stretching every time the wheel is forced against the stop.
    MU-2B series airplanes, both the long and short body, for all 
affected weights and center-of-gravity conditions, require very little 
nose-down trim. A review of FAA data revealed incidents that occurred 
before issuance of AD 93-07-11 and AD 94-04-16 where pilots attempted 
to override the autopilot and inadvertently ran the nose-down trim to 
the down stop. This resulted in excessive control wheel force that 
could only be removed by either manually or electrically trimming the 
nose-down trim back into a normal (or positive) range. AD 93-07-11 and 
AD 94-04-16 reduced the nose-down trim from a range of -10 degrees to a 
-1 degree to -3 degree range. Since the issuance of those ADs, FAA data 
shows no incident involving excessive nose-down trim forces; therefore, 
the FAA disagrees with increasing the trim limit in the nose-down 
direction.
    A stopper limits the travel nut in the trim system preventing any 
cable from stretching. The FAA has not received any reports of any 
needles bending or cables failing.
    We are not changing the AD as a result of this comment.

Comment Issue No. 2: Revised Compliance Time

    Mitsubishi Heavy Industries America, Inc. suggests revising the 
compliance time in paragraph (e)(1)(i) of the AD to add a 6-month 
calendar date limitation in addition to the 100-hour flight time 
limitation since some airplanes fly infrequently. The addition of a 6-
month compliance time would more closely match the compliance time of 
the Japan Civil Aviation Bureau (JCAB) technical circular directive No. 
TCD-3740A-98 and avoid possible confusion for operators.
    We disagree with the commenter. The 100-hour compliance time in 
paragraph (e)(1)(i) is the compliance time for the actions we are 
retaining from AD 94-04-16 and refers to within 100 hours from April 
11, 1994, the effective date of that AD.
    We are not changing this final rule AD action as a result of this 
comment.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
except for minor editorial corrections. In the NPRM we inadvertently 
omitted Model MU-2B-36 from the Applicability section for TCDS A10SW. 
Since that model appears on TCDS A10SW, we are adding it to the 
applicability in case the manufacturer produces serial numbers for this 
model in the future. However, since no serial numbers currently exist 
for this model on TCDS A10SW, adding the model to the applicability 
does not add to the burden of this AD. We have determined that these 
minor corrections:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Costs of Compliance

    We estimate that this AD affects 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 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 modification of the 
elevator trim indicator scale dial:

[[Page 46544]]



----------------------------------------------------------------------------------------------------------------
                                                                                 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 AD.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    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 summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2007-27191; Directorate Identifier 2007-CE-007-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under 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

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

2007-17-09 Mitsubishi Heavy Industries: Amendment 39-15167; Docket 
No. FAA-2007-27191; Directorate Identifier 2007-CE-007-AD.

Effective Date

    (a) This AD becomes effective on September 25, 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 (TCDS A2PC):

------------------------------------------------------------------------
                 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 (TCDS A10SW):

------------------------------------------------------------------------
                 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-36, MU-2B-36A, and  652SA, 661SA and 697SA through
 MU-2B-60.                                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 
reducing the maximum deflection of the elevator nose-down trim to a 
1-degree to 3-degree range from 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.

Compliance

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

[[Page 46545]]



------------------------------------------------------------------------
           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-        the next 100 hours    Mitsubishi Heavy
 degree to 3-degree range.     time-in-service       Industries, Ltd.,
                               (TIS) after April     Service Bulletin
                               11, 1994 (the         No. 216, dated
                               effective date of     September 11, 1992.
                               AD 94-04-16).
                              (ii) For Category 2   (B) For Category 2
                               airplanes: Within     airplanes: Follow
                               the next 100 hours    Mitsubishi Heavy
                               TIS after June 1,     Industries, Ltd.,
                               1993 (the effective   Service Bulletin
                               date of AD 93-07-     No. 079/27-010,
                               11).                  dated August 28,
                                                     1992.
(2) Modify the elevator trim  Within the next 100   (i) For Category 1
 indicator scale dial.         hours TIS after       airplanes: Follow
                               September 25, 2007    Mitsubishi Heavy
                               (the effective date   Industries, Ltd.,
                               of this AD).          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.

Material Incorporated by Reference

    (h) You must use Mitsubishi Heavy Industries, Ltd., Service 
Bulletin No. 216, dated September 11, 1992; Mitsubishi Heavy 
Industries, Ltd., Service Bulletin No. 079/27-010, dated August 28, 
1992; Mitsubishi Heavy Industries, Ltd., Service Bulletin No. 228, 
dated July 13, 1998; and Mitsubishi Heavy Industries, Ltd., Service 
Bulletin No. 091/27-011, dated August 6, 1998; to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Mitsubishi Heavy Industries, Ltd., 
Service Bulletin No. 228, dated July 13, 1998; and Mitsubishi Heavy 
Industries, Ltd., Service Bulletin No. 091/27-011, dated August 6, 
1998; under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On June 1, 1993, the Director of the Federal Register 
approved the incorporation by reference of Mitsubishi Heavy 
Industries, Ltd., Service Bulletin No. 079/27-010, dated August 28, 
1992, listed in this AD.
    (3) On April 11, 1994, the Director of the Federal Register 
approved the incorporation by reference of Mitsubishi Heavy 
Industries, Ltd., Service Bulletin No. 216, dated September 11, 
1992, listed in this AD.
    (4) For service information identified 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.
    (5) You may review copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at 
the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Kansas City, Missouri, on August 14, 2007.
Terry L. Chasteen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-16288 Filed 8-20-07; 8:45 am]
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