Airworthiness Directives; Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D Airplanes, 2439-2442 [2012-604]

Download as PDF Federal Register / Vol. 77, No. 11 / Wednesday, January 18, 2012 / Rules and Regulations List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. pmangrum on DSK3VPTVN1PROD with RULES The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the typecertification basis for the GVI. In lieu of the requirements of § 25.1353(c)(1) through (c)(4) at amendment 25–42, lithium batteries and battery installations on the GVI must be designed and installed as follows: (1) Safe lithium battery-cell temperatures and pressures must be maintained during any charging or discharging condition, and during any failure of the battery-charging or batterymonitoring system not shown to be extremely remote. The lithium-battery installation must preclude explosion in the event of those failures. (2) Design of lithium batteries must preclude the occurrence of selfsustaining, uncontrolled increases in temperature or pressure. (3) No explosive or toxic gases emitted by any lithium battery in normal operation, or as the result of any failure of the battery-charging or batterymonitoring system, or battery installation which is not shown to be extremely remote, may accumulate in hazardous quantities within the airplane. (4) Installations of lithium batteries must meet the requirements of 14 CFR 25.863(a) through (d). (5) No corrosive fluids or gases that may escape from any lithium battery may damage surrounding structure or any adjacent systems, equipment, or electrical wiring of the airplane in such a way as to cause a major or more-severe failure condition, as determined in accordance with 14 CFR 25.1309(b). (6) Each lithium-battery installation must have provisions to prevent any hazardous effect on structure or essential systems caused by the maximum amount of heat the battery can generate during a short circuit of the battery or of its individual cells. (7) Lithium-battery installations must have a system to control automatically the charging rate of the battery to prevent battery overheating or overcharging, and (i) A battery-temperature-sensing and over-temperature-warning system with a means to automatically disconnect the battery from its charging source in the VerDate Mar<15>2010 15:39 Jan 17, 2012 Jkt 226001 event of an over-temperature condition or, (ii) A battery-failure sensing-andwarning system with a means to automatically disconnect the battery from its charging source in the event of battery failure. (8) Any lithium-battery installation, the function of which is required for safe operation of the airplane, must incorporate a monitoring-and-warning feature that will provide an indication to the appropriate flight crewmembers whenever the state-of-charge of the batteries has fallen below levels considered acceptable for dispatch of the airplane. (9) The instructions for continued airworthiness required by § 25.1529 (and § 26.11) must contain maintenance steps to assure that the lithium batteries are sufficiently charged at appropriate intervals specified by the battery manufacturer. The instructions for continued airworthiness must also contain procedures to ensure the integrity of lithium batteries in spares storage to prevent the replacement of batteries, the function of which are required for safe operation of the airplane, with batteries that have experienced degraded charge-retention ability or other damage due to prolonged storage at a low state-ofcharge. Precautions should be included in the continued-airworthiness maintenance instructions to prevent mishandling of lithium batteries, which could result in a short circuit or other unintentional damage that could result in personal injury or property damage. GAC must show compliance with the requirements of these special conditions by test and/or analysis. The aircraft certification office, or its designees, will find compliance in coordination with the FAA Transport Standards Staff. Note 1: The term ‘‘sufficiently charged’’ means that the battery retains enough of a charge, expressed in ampere-hours, to ensure that the battery cells are not damaged. A battery cell may be damaged by reducing the battery’s charge below a point where the battery’s ability to charge and retain a full charge is reduced. This reduced charging and charge-retention capability would be greater than the reduction that may result from normal operational degradation. Note 2: These special conditions are not intended to replace § 25.1353(c) in the certification basis of the GVI. These special conditions apply only to lithium batteries and rechargeable lithium-battery-system installations. The requirements of § 25.1353(c) remain in effect for batteries and battery installations on the GVI that do not use lithium batteries. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 2439 Issued in Renton, Washington, on January 9, 2012. K.C. Yanamura, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–798 Filed 1–17–12; 8:45 am] BILLING CODE 4910–13–P 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: 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: SUMMARY: E:\FR\FM\18JAR1.SGM 18JAR1 2440 Federal Register / Vol. 77, No. 11 / Wednesday, January 18, 2012 / Rules and Regulations • 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: pmangrum on DSK3VPTVN1PROD with RULES • 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 bobweight 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. VerDate Mar<15>2010 15:39 Jan 17, 2012 Jkt 226001 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 Communique #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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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 overcenter 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: E:\FR\FM\18JAR1.SGM 18JAR1 Federal Register / Vol. 77, No. 11 / Wednesday, January 18, 2012 / Rules and Regulations 2441 ESTIMATED COSTS Cost per product Action Labor cost Parts cost Inspection of the elevator bob-weight and attaching linkage. 1 work-hour × $85 per hour = $85 ........... Not applicable ........... 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. pmangrum on DSK3VPTVN1PROD with RULES 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. 15:39 Jan 17, 2012 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. § 39.13 [Amended] 2. The FAA amends § 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 Regulatory Findings VerDate Mar<15>2010 Adoption of the Amendment Jkt 226001 None. (c) Applicability This AD applies to the following Hawker Beechcraft Corporation airplanes, certificated in any category: Models Serial Nos. (1) 1900 ............ (2) 1900C ......... UA–3. UB–1 through UB–74 and UC–1 through UC–174. UD–1 through UD–6. (3) 1900C (Military). (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. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 $85 Cost on U.S. operators $25,500 (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 ´ Communique #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 Communique #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 ´ Communique 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 FAAapproved 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 E:\FR\FM\18JAR1.SGM 18JAR1 2442 Federal Register / Vol. 77, No. 11 / Wednesday, January 18, 2012 / Rules and Regulations 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. DEPARTMENT OF TRANSPORTATION (j) Related Information AGENCY: 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 pmangrum on DSK3VPTVN1PROD with RULES (1) You must use Hawker Beechcraft ´ Corporation Safety Communique #321, dated December 2011, to do the actions required by this AD, unless the AD specifies otherwise. ´ The Safety Communique #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 VerDate Mar<15>2010 15:39 Jan 17, 2012 Jkt 226001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1221; Directorate Identifier 2008–NM–097–AD; Amendment 39–16881; AD 2011–25–05] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. We are adopting a new airworthiness directive (AD) for The Boeing Company Model 767 airplanes. This AD requires installing new panel assemblies in the main equipment center or on the forward cargo compartment sidewall and removing certain relays from some panels in the main equipment center. This AD also requires revising the maintenance program to incorporate Airworthiness Limitations (AWLs) No. 28–AWL–27 and No. 28–AWL–28. This AD also includes an alternative location for the installation of the new panel assemblies for airplanes that have the optional water system drain plumbing and changing the interconnecting wiring between the P141 panel and the P36 and P37 panels. For airplanes with a deactivated center fuel tank, this AD also requires an alternative functional test for the left and right override/ jettison pumps. We are issuing this AD to prevent possible sources of ignition in a fuel tank caused by electrical fault or uncommanded dry operation of the main tank boost pumps and center auxiliary tank override and jettison pumps. This AD was prompted by fuel system reviews conducted by the manufacturer. An ignition source in the fuel tank could result in a fire or an explosion and consequent loss of the airplane. SUMMARY: This AD is effective February 22, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of February 22, 2012. The Director of the Federal Register previously approved the incorporation by reference of certain other publications listed in this AD as of January 12, 2010 (74 FR 68515, December 28, 2009). The Director of the Federal Register previously approved the incorporation by reference of certain other publications listed in this AD as of DATES: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 September 9, 2009 (74 FR 38905, August 5, 2009). For service information identified in this AD contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone (206) 544–5000, extension 1; fax (206) 766–5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call (425) 227– 1221. 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 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: Elias Natsiopoulos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6478; fax: (425) 917–6590; email: elias.natsiopoulos@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That supplemental NPRM published in the Federal Register on April 5, 2011 (76 FR 18664). That supplemental NPRM proposed to require installing new panel assemblies in the main equipment center or on the forward cargo compartment sidewall and removing certain relays from some panels in the main equipment center. That supplemental NPRM also proposed to require revising the maintenance program to incorporate Airworthiness Limitations (AWLs) No. 28–AWL–27 and No. 28–AWL–28. For certain airplanes that supplemental NPRM proposed to require prior or concurrent E:\FR\FM\18JAR1.SGM 18JAR1

Agencies

[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.

-----------------------------------------------------------------------

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
----------------------------------------------------------------------------------------------------------------
                                                                                     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.
----------------------------------------------------------------------------------------------------------------

    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