[Federal Register Volume 78, Number 137 (Wednesday, July 17, 2013)]
[Proposed Rules]
[Pages 42724-42727]
From the Federal Register Online via the Government Publishing 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:
[email protected].
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: [email protected].
(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]
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