Airworthiness Directive · Amendment 39-17731 · Flight controls
Beechcraft Corporation Airplanes
This AD applies to the following Beechcraft Corporation airplanes in table 1 to paragraph (c) of this AD, 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. |
We are superseding Airworthiness Directive (AD) 2011-27-51 for certain Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. AD 2011-27-51 required 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 requires 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. We are issuing this AD to correct the unsafe condition on these products.
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 Communiqué 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 Communiqué 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 Communiqué 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.
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.
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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
