2014-02-03: Flight Controls

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: [[Page 5256]] 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: 2014-02-03 Beechcraft Corporation: Amendment 39-17731 ; Docket No. FAA-2013-0611; Directorate Identifier 2013-CE-019-AD. (a) Effective Date This AD is effective March 7, 2014. (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 in table 1 to paragraph (c) of this AD, certificated in any category:Table 1 to Paragraph (c) of This AD--Applicability ------------------------------------------------------------------------ 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 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) from 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. (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. 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 thestabilizer 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 March 7, 2014 (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, 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 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. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on March 7, 2014. (i) Beechcraft Corporation Mandatory Service Bulletin No. SB 27- 4119, dated June 2013. (ii) Reserved. (4) The following service information was approved for IBR on January 18, 2012 (77 FR 2439, January 18, 2012). (i) Hawker Beechcraft Corporation Safety Communiqu[eacute] No. 321, dated December 2011. (ii) Reserved. (5) 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. (6) 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. (7) You may view this 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.