AD 2001-18-07

[Federal Register Volume 66, Number 173 (Thursday, September 6, 2001)]
[Rules and Regulations]
[Pages 46515-46517]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-22174]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-20-AD; Amendment 39-12433; AD 2001-18-07]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Beech Models 
1900, 1900C, and 1900D 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 Raytheon Aircraft Company (Raytheon) Beech Models 
1900, 1900C, and 1900D airplanes. This AD requires you to inspect all 
four flap flexible shaft assemblies for the correct diagonal wrap and 
the correct installation. This AD also requires you to replace any flap 
flexible shaft assembly that has an incorrect diagonal wrap or 
incorrect installation. This AD is the result of several occurrences of 
flap extension/retraction failures on the affected airplanes due to the 
inner flexible shaft ends separating or disengaging. The actions 
specified by this AD are intended to prevent these flap extension/
retraction failures due to incorrectly configured flap flexible shaft 
assemblies. Such failure could result in an asymmetric flap condition 
during flight if the flap safety switch fails to function properly.

DATES: This AD becomes effective on October 12, 2001.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
October 12, 2001.

ADDRESSES: You may get the service information referenced in this AD 
from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140. You may view this 
information at the Federal Aviation Administration (FAA), Central 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2001-CE-20-AD, 901 Locust, Room 506, 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: Paul DeVore, Aerospace Engineer, FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone: (316) 946-4142; facsimile: 
(316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

    The FAA has received reports of flap extension/retraction system 
failures on Raytheon Model 1900D airplanes. The failures occurred when 
the inner flexible shaft ends separated or disengaged. One of these 
failures resulted in an asymmetric flap condition when the flap safety 
switch failed to function properly.
    The flap flexible shafts are designed to carry more torque in one 
direction than the other. If installed on the wrong side of the 
airplane, the excessive torque load leads to these failures. Raytheon 
informed us that the flap flexible shafts may have been installed on 
the wrong side of the airplane on certain Beech Models 1900, 1900C, and 
1900D airplanes.

What Are the Consequences if the Condition Is Not Corrected?

    Flap extension/retraction failures caused by incorrectly configured 
flap flexible shaft assemblies could result in loss of flap function or 
an asymmetric flap condition during flight if the flap safety switch 
fails to function properly.

Has FAA Taken Any Action to This Point?

    The FAA 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 Raytheon Beech Models 1900, 1900C, and 1900D airplanes. This 
proposal was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on June 5, 2001 (66 FR 30093). The NPRM proposed to 
require you to inspect the inner flexible (drive) shaft of all four 
flap flexible shaft assemblies for the correct diagonal wrap and the 
correct installation; and replace any flap flexible shaft assembly that 
has an incorrect diagonal wrap or incorrect installation.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. We did not receive any comments on the proposed rule 
or on our determination of the cost to the public.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We 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

How Many Airplanes Does This AD Impact?

    The FAA estimates that this AD affects 205 airplanes in the U.S. 
registry.

What Is the Cost Impact of This AD on Owners/Operators of the 
Affected airplanes?

    We estimate the following costs to accomplish the inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                                   Total cost on
            Labor cost                   Parts cost               Total cost per airplane         U.S. operators
----------------------------------------------------------------------------------------------------------------
2 workhours  x  $60 per hour =      No parts required     $120 per airplane.....................         $24,600
 $120.                               for the inspection.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
replacements that will be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such replacements.

[[Page 46516]]


------------------------------------------------------------------------
                                                         Cost per flap
           Labor cost                 Parts cost             shaft
------------------------------------------------------------------------
8 workhours per flap shaft  x     $232 per flap       $712 per flap
 $60 per hour = $480.              shaft.              shaft (total of
                                                       four per
                                                       airplane).
------------------------------------------------------------------------

    The manufacturer will provide warranty credit for labor and parts 
to the extent noted under the Warranty Credit section of Raytheon 
Mandatory Service Bulletin SB 27-3397, Issued: January, 2001.

Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    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 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, 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

    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. FAA amends Sec. 39.13 by adding a new AD to read as follows:

    2001-18-07  Raytheon Aircraft Company: Amendment 39-12433; 
Docket No. 2001-CE-20-AD.

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category:

------------------------------------------------------------------------
                 Model                              Serial No.
------------------------------------------------------------------------
Beech Model 1900.......................  UA-2 and UA-3.
Beech Model 1900C......................  UB-1 through UB-74 and UC-1
                                          through UC-174.
Beech Model 1900C (C-12J)..............  UD-1 through UD-6.
Beech Model 1900D......................  UE-1 through UE-345; UE-347
                                          through UE-361; UE-364; UE-
                                          367; UE-373; and UE-379.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes must comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to prevent flap extension/retraction failures 
due to incorrectly configured flap flexible shaft assemblies. Such 
failure could result in an asymmetric flap condition during flight 
if the flap safety switch fails to function properly.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Inspect the inner flexible    Within the next     In accordance with
 (drive) shaft of all four flap    200 hours time-in-  the
 flexible shaft assemblies for     service (TIS)       ACCOMPLISHMENT
 the correct diagonal wrap and     after October 12,   INSTRUCTIONS
 the correct installation.         2001 (the           section of
                                   effective date of   Raytheon Aircraft
                                   this AD), unless    Mandatory Service
                                   already             Bulletin SB 27-
                                   accomplished.       3397, Issued:
                                                       January, 2001.
(2) Replace any flap flexible     Prior to further    In accordance with
 shaft assembly found to-have an   flight after the    the
 incorrect diagonal wrap or        inspection          ACCOMPLISHMENT
 incorrect installation during     required in         INSTRUCTIONS
 the inspection required by        paragraph (d)(1)    section of
 paragraph (d)(1) of this AD.      of this AD.         Raytheon Aircraft
                                                       Mandatory Service
                                                       Bulletion SB 27-
                                                       3397, Issued:
                                                       January, 2001,
                                                       and applicable
                                                       maintenance
                                                       manual.
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Wichita Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Wichita ACO.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Paul DeVore, Aerospace 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4142; facsimile: (316) 946-4407.

[[Page 46517]]

    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) Are any service bulletins incorporated into this AD by 
reference? You must accomplish the actions required by this AD in 
accordance with Raytheon Aircraft Mandatory Service Bulletin SB 27-
3397, Issued: January, 2001. The Director of the Federal Register 
approved this incorporation by reference under 5 U.S.C. 552(a) and 1 
CFR part 51. You can get copies from Raytheon Aircraft Company, P.O. 
Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or 
(316) 676-3140. You can look at copies at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, 
Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW, suite 700, Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on October 12, 2001.

    Issued in Kansas City, Missouri, on August 28, 2001.
Larry E. Werth,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-22174 Filed 9-5-01; 8:45 am]
BILLING CODE 4910-13-U