
[Federal Register Volume 78, Number 137 (Wednesday, July 17, 2013)]
[Proposed Rules]
[Pages 42724-42727]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-17146]


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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]
RIN 2120-AA64


Airworthiness Directives; Beechcraft Corporation Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2011-27-
51 that applies to certain Beechcraft Corporation Models 1900, 1900C, 
and 1900D airplanes. AD 2011-27-51 currently requires 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. Since we issued AD 2011-27-51, a 
secondary elevator bob-weight stop bolt has been designed. This 
proposed AD would require 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, which could result in 
loss of control. We are proposing this AD to correct the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by September 3, 
2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room

[[Page 42725]]

W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    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; 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION 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.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0611; 
Directorate Identifier 2013-CE-019-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On January 6, 2012, we issued AD 2011-27-51, Amendment 39-16915 (77 
FR 2439, January 18, 2012), for certain Hawker Beechcraft Corporation 
Models 1900, 1900C, and 1900D airplanes. AD 2011-27-51 requires 
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. AD 2011-27-51 resulted 
from 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. We 
issued AD 2011-27-51 to detect and correct conditions that could result 
in reduced nose down elevator control and loss of control.

Actions Since AD 2011-27-51 Was Issued

    Since we issued AD 2011-27-51 (77 FR 2439, January 18, 2012), 
Beechcraft Corporation designed a secondary elevator bob-weight stop 
bolt to reduce the possibility of the bob-weight from traveling past 
the stop bolt.

Relevant Service Information

    We reviewed Hawker Beechcraft Corporation Safety Communiqu[eacute] 
No. 321, dated December 2011, and Beechcraft Corporation Mandatory 
Service Bulletin No. SB 27-4119, dated June 2013. The service 
information describes procedures for inspecting the elevator bob-weight 
and attaching linkage for correct installation and for damage or 
deformation to the weight and/or weight bracket. The service 
information also describes procedures for installing the secondary 
elevator bob-weight stop bolt, Kit 114-5060.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2011-
27-51 (77 FR 2439, January 18, 2012). This proposed AD would also add 
the requirement to install the secondary elevator bob-weight stop bolt, 
Kit 114-5060.

Costs of Compliance

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

                                                 Estimated Costs
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                                                                                     Cost per      Cost on U.S.
             Action                  Labor cost              Parts cost               product        operators
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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.
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    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

[[Page 42726]]

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),
    (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.

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

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:

Beechcraft Corporation: Docket No. FAA-2013-0611; Directorate 
Identifier 2013-CE-019-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by September 3, 
2013.

(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, certificated in any category:

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               Models                                                 Serial Nos.
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(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.
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(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) 
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 (which is 
incorporated by reference in AD 2011-27-51).
    (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.

    Note 1 to paragraphs (g)(1) and (g)(2) of this AD:  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 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,

[[Page 42727]]

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

    (1) 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.
    (2) 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.

    Issued in Kansas City, Missouri, on July 11, 2013.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2013-17146 Filed 7-16-13; 8:45 am]
BILLING CODE 4910-13-P


