Daily Rules, Proposed Rules, and Notices of the Federal Government
For service information identified in this proposed AD, contact Hawker Beechcraft Corporation, B091-A04, 10511 E. Central Ave., Wichita, Kansas 67206; telephone: 1 (800) 429-5372 or (316) 676-3140; fax: (316) 676-8027; email:
You may examine the AD docket on the Internet at
We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the
We will post all comments we receive, without change, to
We received reports of elevator balance weights becoming loose or failing on Hawker Beechcraft Model 58 airplanes. The balance weight material was under strength and did not meet the material specification requirements. The balance weight looseness and/or failure could reduce the flutter speed and lead to loss of control.
We reviewed Hawker Beechcraft Mandatory Service Bulletin SB 55-4089, Revision 1, dated February, 2012. Hawker Beechcraft Mandatory Service Bulletin SB 55-4089, Revision 1, dated February, 2012, describes procedures for inspection and replacement of the elevator balance weight assembly.
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 designs.
This proposed AD would require accomplishing the actions specified in the service information described previously.
The service information specifies an inspection of the elevator balance weight with an optional replacement. This proposed AD requires that the elevator balance weight be replaced within 200 hours time-in-service (TIS) after the effective date of this proposed AD, with a 100-hour TIS inspection before the replacement.
We estimate that this proposed AD affects 343 airplanes of U.S. registry.
We estimate the following costs to comply with this proposed AD:
According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate.
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.
We 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.
(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.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
1. The authority citation for part 39 continues to read as follows:
49 U.S.C. 106(g), 40113, 44701.
2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
We must receive comments by December 21, 2012.
This AD applies to the following Hawker Beechcraft Corporation (HBC) airplanes, certificated in any category:
(1) Model 58, serial numbers TH-1768 through TH-2110; and
(2) Models 58, 58TC, 58P, 95C55, E55, and 56TC that are equipped with elevator balance weight assemblies purchased between January 1, 1996, and December 31, 2005.
Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 2730: Elevator Balance Weight.
This AD was prompted by reports of reports of elevator balance weights becoming loose or failing because the balance weight material was under strength and did not meet material specifications. We are issuing this AD to prevent the elevator balance weights from becoming lose or failing, which could result in reduced flutter speed and lead to loss of control.
Comply with this AD within the compliance times specified, unless already done, following the instructions in Hawker Beechcraft Mandatory Service Bulletin SB 55-4089, Revision 1, dated February, 2012.
Before further flight after the effective date of this AD and thereafter at intervals not to exceed 100 hours time-in-service (TIS) until the replacement required by this AD is done, inspect the elevator balance weights for looseness, failure, and/or working (smoking) fasteners and inserts.
(1) Replace the defective elevator balance weight with an airworthy balance weight as specified in Hawker Beechcraft Mandatory Service Bulletin SB 55-4089, Revision 1, dated February, 2012, at whichever of the following occurs first:
(i) Before further flight after any inspection required by paragraph (g) of this AD where any looseness, failure, and/or working (smoking) fasteners and inserts are found; or,
(ii) Within the next 200 hours TIS after the effective date of this AD.
(2) Replacement of the elevator balance weights with airworthy elevator balance weights terminates the 100-hour inspection requirement in paragraph (g) of this AD.
(3) If only one elevator balance weight is replaced before 200 hours TIS after the effective date of this AD, then the other elevator balance weight is subject to the repetitive inspections until the replacement required by paragraph (h)(1) of this AD.
Special flight is permitted with the following limitations: Maximum structural cruising speed (V
(1) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.
(1) For more information about this AD, contact Steven E. Potter, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4124; fax: (316) 946-4107; email:
(2) For service information identified in this AD, contact Hawker Beechcraft Corporation, B091-A04, 10511 E. Central Ave., Wichita, Kansas 67206; telephone: 1 (800) 429-5372 or (316) 676-3140; fax: (316) 676-8027; email: