Document ID: FAA-2012-0014-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Hawker Beechcraft Corp. Models 1900, 1900C, and 1900D Airplanes
Posted Date: 2012-01-18T05:00Z

[Federal Register Volume 77, Number 11 (Wednesday, January 18, 2012)]
[Rules and Regulations]
[Pages 2439-2442]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-604]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0014; Directorate Identifier 2011-CE-044-AD; 
Amendment 39-16915; AD 2011-27-51]
RIN 2120-AA64

Airworthiness Directives; Hawker Beechcraft Corporation Models 
1900, 1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. 
This emergency AD was sent previously to all known U.S. owners and 
operators of these airplanes. This AD 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. This AD was prompted by reports of the 
elevator bob-weight (stabilizer weight) traveling past its stop bolt, 
which allowed the attaching linkage to move over-center, resulting in 
reduced nose down elevator control, which could result in loss of 
control of the airplane. We are issuing this AD to detect and correct 
conditions that could result in reduced nose down elevator control and 
loss of control of the airplane.

DATES: This AD is effective January 18, 2012 to all persons except 
those persons to whom it was made immediately effective by Emergency AD 
2011-27-51, issued on December 23, 2011, which contained the 
requirements of this amendment.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication identified in the AD as of January 
18, 2012.
    We must receive comments on this AD by March 5, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 2440]]

     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 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 Hawker 
Beechcraft Corporation at P.O. Box 85, Wichita, Kansas 67201-0085; 
telephone: (800) 429-5372 or (316) 676-3140; Internet: http://pubs.hawkerbeechcraft.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations Office 
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 street address for 
the Docket Operations 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 ONE OF THE FOLLOWING:

 Paul DeVore, Aerospace Engineer, Wichita ACO, FAA, 1801 
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4142; fax: (316) 946-4107; email: paul.devore@faa.gov; or
 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:

Discussion

    On December 23, 2011, we issued Emergency AD 2011-27-51, which 
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. This AD was 
prompted by the following reports of the elevator bob-weight 
(stabilizer weight) traveling past its stop bolt, which allowed the 
attaching linkage to move over-center, reducing nose down elevator 
control.
    In one instance, a Model 1900C airplane experienced jammed 
elevators on take-off after a loud bang was heard in the cockpit 
shortly after rotation. The flight crew noticed that they were unable 
to move the control column to a nose down position. Elevator movement 
was only available between neutral to full deflection nose up. The 
airplane pitch was controlled with the elevator trim and the airplane 
returned to base, landing safely. Upon inspection, mechanics noticed 
that the bob-weight interconnect link, part number (p/n) 101-524112-1, 
was upside down and trailing forward from the control column weld 
assembly instead of trailing aft as it should. With the link traveled 
over-center, the geometry of the bob-weight was completely changed 
relative to its stop. This condition made the bob-weight hit its stop 
mid-travel, where it should actually have positive clearance from its 
stop at the full nose down position. The elevator could now only move 
between nose full up and neutral.
    In another instance, on a Model 1900D airplane, during the takeoff 
roll the elevator controls felt heavy and appeared to be jammed/
sticking, requiring more force than usual to rotate. The crew then 
aborted the takeoff run. Subsequent investigation revealed that the 
elevator bob-weight attaching link assembly traveled over-center, thus 
preventing full nose down elevator control authority.
    The Model 1900 airplanes have the same type design and thus are 
subject to this unsafe condition.
    This condition, if not corrected, could result in reduced nose down 
elevator control and loss of airplane control.

Relevant Service Information

    We reviewed Hawker Beechcraft Corporation Safety Communiqu[eacute] 
321, dated December 2011. The service information provides 
information to assist in doing the actions of this AD.

FAA's Determination

    We are issuing 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.

AD Requirements

    This AD 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.

Interim Action

    We consider this AD interim action to address the immediate unsafe 
condition affecting these airplanes. We may take further AD action at a 
later date.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because the 
elevator stabilizer weight (bob-weight) could move over-center 
resulting in reduced nose down elevator control, which could result in 
loss of control of the airplane. Therefore, we find that notice and 
opportunity for prior public comment are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2012-0014 and 
Directorate Identifier 2011-CE-044-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
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 AD.

Costs of Compliance

    We estimate that this AD affects 300 airplanes.
    We estimate the following costs to comply with this AD:

[[Page 2441]]

                                                 Estimated Costs
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                                                                                     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         $25,500
 weight and attaching linkage.    per hour = $85.
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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.

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

    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:

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 adding the following new airworthiness 
directive (AD):

2011-27-51 Hawker Beechcraft Corporation: Amendment 39-16915 ; 
Docket No. FAA-2012-0014; Directorate Identifier 2011-CE-044-AD.

(a) Effective Date

    This AD is effective January 18, 2012, to all persons except 
those persons to whom it was made immediately effective by Emergency 
AD 2011-27-51, issued on December 23, 2011, which contained the 
requirements of this amendment.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the following Hawker Beechcraft Corporation 
airplanes, certificated in any category:

------------------------------------------------------------------------
                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, which allowed the 
attaching linkage to move over-center. We are issuing this AD to 
detect and correct conditions that could result in reduced nose down 
elevator control and loss of control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspections

    Within the next 10 hours time-in-service after January 18, 2012 
(the effective date of this AD), inspect the elevator bob-weight 
installation for the following conditions. Use Hawker Beechcraft 
Corporation Safety Communiqu[eacute] 321, dated December 
2011.

    Note: 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] 
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.
    (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) Corrective Actions

    If any discrepancies are found in the inspections required in 
paragraph (g) of this AD, before further flight, do the following:
    (1) Contact Hawker Beechcraft Corporation Technical Support by 
telephone at (800) 429-5372 or (316) 676-3140 to obtain FAA-approved 
repair or replacement instructions.
    (2) Incorporate the repair or replacement specified in the FAA-
approved instructions.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if

[[Page 2442]]

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.

(j) Related Information

    For more information about this AD, contact one of the 
following:
    (i) Paul DeVore, Aerospace Engineer, Wichita ACO, FAA, 1801 
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4142; fax: (316) 946-4107; email: paul.devore@faa.gov; or
    (ii) 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.

(k) Material Incorporated by Reference

    (1) You must use Hawker Beechcraft Corporation Safety 
Communiqu[eacute] 321, dated December 2011, to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Safety Communiqu[eacute] 321 references Hawker Beechcraft 
Corporation Mandatory Service Bulletin 27-3739, but that service 
bulletin is not required to do the actions of this AD. The Director 
of the Federal Register approved the incorporation by reference 
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Hawker Beechcraft Corporation at P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140; Internet: http://pubs.hawkerbeechcraft.com.
    (3) You may review copies of the 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.
    (4) You may also review copies of the 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 6, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012-604 Filed 1-17-12; 8:45 am]
BILLING CODE 4910-13-P