Document ID: FAA-2013-0611-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Beechcraft Corporation Airplanes
Posted Date: 2014-01-31T05:00Z

[Federal Register Volume 79, Number 21 (Friday, January 31, 2014)]
[Rules and Regulations]
[Pages 5254-5256]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-01832]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0611; Directorate Identifier 2013-CE-019-AD; 
Amendment 39-17731; AD 2014-02-03]
RIN 2120-AA64

Airworthiness Directives; Beechcraft Corporation Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2011-27-51 for 
certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. 
AD 2011-27-51 required inspecting the elevator bob-weight and attaching 
linkage for correct installation and for damage or deformation to the 
weight and/or weight bracket with corrective action as necessary. This 
AD requires installation of the secondary elevator bob-weight stop 
bolt. The elevator bob-weight (stabilizer weight) traveling past its 
stop bolt may allow the attaching linkage to move over-center and lead 
to reduced nose down elevator control. We are issuing this AD to 
correct the unsafe condition on these products.

DATES: This AD is effective March 7, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 7, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 18, 2012 (77 FR 2439, January 18, 2012).

ADDRESSES: For service information identified in this AD, contact 
Beechcraft Corporation at P.O. Box 85, Wichita, Kansas 67201-0085; 
telephone: (800) 429-5372 or (316) 676-3140; Internet: http://www.beechcraft.com. Beechcraft Corporation publishes service 
information for the Beechcraft Corporation airplanes affected by this 
AD action. You may review copies of the referenced service information 
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, 
Missouri 64106. For information on the availability of this material at 
the FAA, call (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0611; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Don Ristow, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 
100, Wichita, Kansas 67209; telephone: (316) 946-4120; fax: (316) 946-
4107; email: donald.ristow@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-27-51, Amendment 39-16915 (77 FR 2439, 
January 18, 2012), (``AD 2011-27-51''). AD 2011-27-51 applied to 
certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. 
The NPRM published in the Federal Register on July 17, 2013 (78 FR 
42724). The NPRM proposed to retain all of the requirements of AD 2011-
27-51 and add the requirement to install the secondary elevator bob-
weight stop bolt, Kit 114-5060. We are issuing this AD to

[[Page 5255]]

prevent the elevator bob-weight (stabilizer weight) from traveling past 
its stop bolt and allowing the attaching linkage to move over-center 
and lead to reduced nose down elevator control, which could result in 
loss of control.

Comments

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

Requested Change to Compliance Time

    Pat Kremer requested we change the compliance time for installing 
the secondary elevator bob-weight stop bolt Kit 114-5060 from 600 hours 
time-in-service (TIS) to 1,200 hours TIS or 24 months to coincide with 
the continuous inspection program for the Model 1900C airplanes. This 
requested change would minimize the impact or down time for the 
airplanes.
    We disagree with this comment. We do not believe that 1,200 hours 
TIS or 24 months will adequately mitigate the unsafe condition on the 
entire affected airplane fleet. We determined that 600 hours TIS is the 
appropriate compliance time to address the identified unsafe condition. 
The proposed compliance time change may be adequate to address the 
unsafe condition on certain individual airplanes, and the FAA will 
evaluate any alternative method of compliance (AMOC) request we receive 
as specified in paragraph (j) of this AD.
    We did not make any changes to this final rule AD action based on 
this comment.

Requested Clarification of Kit Instructions

    Travis Reinhardt requested the service information specify that a 
collar be used with the optional Hi-Lok pin. He also requested the 
service information contain better instructions for inhibiting and un-
inhibiting the control system during installation of the secondary 
elevator bob-weight stop bolt Kit 114-5060.
    We agree with this comment. The collar should be specified to 
provide complete instructions for installation of the secondary 
elevator bob-weight stop bolt Kit 114-5060. The manufacturer has 
revised the kit installation instructions to specify the collar for use 
with the optional Hi-Lok pin and to clarify the intent for inhibiting 
the control system during installation of the kit. However, these 
clarification changes to the kit installation instructions do not 
affect the language used in this AD action or require any additional 
action for those airplanes that previously had the kit incorporated.
    We did not make any changes to the actions required in this final 
rule AD action based on this comment.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 42724, July 17, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 42724, July 17, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 165 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
             Action                  Labor cost              Parts cost               product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of the elevator bob-  1 work-hour x $85  Not applicable..............             $85         $14,025
 weight and attaching linkage.    per hour = $85.
Installation of the secondary    4 work-hours x     $2,740......................           3,080         508,200
 elevator bob-weight stop bolt,   $85 per hour =
 Kit 114[dash]5060.               $340.
----------------------------------------------------------------------------------------------------------------

    The on-condition costs for any corrective action that may be 
necessary based on the above inspection would vary from airplane to 
airplane, and we have no way of determining that cost.
    The cost of the inspection is a retained cost from AD 2011-27-51 
(77 FR 2439, January 18, 2012) and does not add a burden over what was 
already imposed.

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 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 DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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 FAA amends 14 CFR part 39 as follows:

[[Page 5256]]

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) 
2011-27-51, Amendment 39-16915 (77 FR 2439, January 18, 2012), and 
adding the following new AD:

2014-02-03 Beechcraft Corporation: Amendment 39-17731 ; Docket No. 
FAA-2013-0611; Directorate Identifier 2013-CE-019-AD.

(a) Effective Date

    This AD is effective March 7, 2014.

(b) Affected ADs

    This AD supersedes AD 2011-27-51, Amendment 39-16915 (77 FR 
2439, January 18, 2012).

(c) Applicability

    This AD applies to the following Beechcraft Corporation 
airplanes in table 1 to paragraph (c) of this AD, certificated in 
any category:

           Table 1 to Paragraph (c) of This AD--Applicability
------------------------------------------------------------------------
               Models                             Serial Nos.
------------------------------------------------------------------------
(1) 1900............................   UA-3.
(2) 1900C...........................  UB-1 through UB-74 and UC-1
                                       through UC-174.
(3) 1900C (Military)................  UD-1 through UD-6.
(4) 1900D...........................  UE-1 through UE-439.
------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

    This AD was prompted by reports of the elevator bob-weight 
(stabilizer weight) traveling past its stop bolt and allowing the 
attaching linkage to move over-center, which could lead to reduced 
nose down elevator control. Also, Beechcraft Corporation designed a 
secondary elevator bob-weight stop bolt to reduce the possibility of 
the bob-weight from traveling past the stop bolt. We are issuing 
this AD to prevent the elevator bob-weight (stabilizer weight) from 
traveling past its stop bolt and allowing the attaching linkage to 
move over-center and lead to reduced nose down elevator control, 
which could result in loss of control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done. Paragraph (g) of this AD only applies to 
airplanes where the inspection required by AD 2011-27-51 (77 FR 
2439, January 18, 2012) has not been done.

(g) Retained Inspections

    Within the next 10 hours time-in-service (TIS) after January 18, 
2012 (the effective date of AD 2011-27-51 (77 FR 2439, January 18, 
2012)), inspect the elevator bob-weight installation for the 
following conditions specified in paragraphs (g)(1) through (g)(4) 
in this AD. Use Hawker Beechcraft Corporation Safety 
Communiqu[eacute] No. 321, dated December 2011.
    (1) The correct positioning of the elevator control column link 
assembly, (part number (P/N) 101-524112-1 (1900/1900C) or P/N 101-
524112-5 (1900D)). With the elevator control column in the full nose 
down position (control column forward), the link must form an angle 
between the link attachment point at the control column and the bell 
crank pivot point as shown in the Hawker Beechcraft Corporation 
Safety Communiqu[eacute] photo labeled ``Correct Link Orientation.'' 
The link should be trailing aft from the control column assembly. 
The term ``nose down'' corresponds to the airplane nose down, down 
elevator, and control column forward position as used in this AD and 
Hawker Beechcraft Corporation Safety Communiqu[eacute] No. 321, 
dated December 2011.
    (2) The clearance of the bob-weight stop bolt. With the elevator 
control column in the full nose down position (control column 
forward), the stabilizer weight stop bolt must have positive 
clearance with the face of the stabilizer weight.
    (3) The condition of the bob-weight and alignment with the stop 
bolt. Inspect for evidence of scraping along either side of the 
weight by the stop bolt. With side pressure applied by hand to the 
stabilizer weight, no part of the stop bolt should protrude beyond 
the face of the stabilizer weight on either edge.
    (4) The condition of the bob-weight support bracket. Inspect for 
evidence of damage or deformation by contact with the weight 
assembly.

(h) Installation of Kit 114-5060

    Within the next 600 hours TIS after March 7, 2014 (the effective 
date of this AD), install the secondary elevator bob-weight stop 
bolt, Kit 114-5060, following Beechcraft Corporation Mandatory 
Service Bulletin No. SB 27-4119, dated June 2013.

(i) Corrective Actions

    If any discrepancies are found during the inspection required in 
paragraph (g) of this AD, including all subparagraphs, and during 
the installation required in paragraph (h) of this AD, before 
further flight, contact Beechcraft Corporation Technical Support. If 
a deviation from FAA-approved type design is required, then request 
an alternative method of compliance (AMOC) as described in paragraph 
(j) of this AD. You may contact Beechcraft Technical Support by 
telephone at (800) 429-5372 or (316) 676-3140.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) AMOCs approved for AD 2011-27-51 (77 FR 2439, January 18, 
2012) are approved as AMOCs for the corresponding provisions of this 
AD.

(k) Related Information

    For more information about this AD, contact Don Ristow, 
Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4120; fax: (316) 946-
4107; email: donald.ristow@faa.gov.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
March 7, 2014.
    (i) Beechcraft Corporation Mandatory Service Bulletin No. SB 27-
4119, dated June 2013.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
January 18, 2012 (77 FR 2439, January 18, 2012).
    (i) Hawker Beechcraft Corporation Safety Communiqu[eacute] No. 
321, dated December 2011.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Beechcraft Corporation at P.O. Box 85, Wichita, Kansas 67201-0085; 
telephone: (800) 429-5372 or (316) 676-3140; Internet: http://www.beechcraft.com.
    (6) You may review copies of the referenced service information 
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, 
Missouri 64106. For information on the availability of this material 
at the FAA, call (816) 329-4148.
    (7) You may view this service information that is incorporated 
by reference 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/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on January 15, 2014.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-01832 Filed 1-30-14; 8:45 am]
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