Airworthiness Directive · Amendment 39-14426 · Bombardier Model DHC-8-400 Series Airplanes
Bombardier Model DHC-8-400 Series Airplanes
This AD applies to Bombardier Model DHC-8-400 series airplanes, certificated in any category; serial numbers 4001, and 4003 through 4081 inclusive.
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires an inspection of the laminated shims for cracks, damage, or extrusion between the forward attachment fittings of the horizontal stabilizer and the top rib of the vertical stabilizer; a torque check of the attachment bolts in the attachment fittings of the front, middle, and rear spars; and corrective actions if necessary. This AD results from a report indicating that delaminated shims extruded from the interface between the forward attaching fittings of the horizontal stabilizer and the top rib of the vertical stabilizer, and that inadequate torque values of some bolts were found. We are issuing this AD to prevent reduced structural integrity of the horizontal stabilizer, and consequent loss of controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Bombardier Service Bulletin 84-55-02, Revision “A,” dated January 12, 2005.
(g) Accomplishing a detailed inspection, a breakaway torque check, and corrective actions if necessary before the effective date of this AD in accordance with Bombardier Service Bulletin 84-55-02, dated December 11, 2003; or Bombardier All Operator Message 096B, dated June 12, 2003; is acceptable for compliance with the corresponding requirements of this AD.
(h) Accomplishing the repair before the effective date of this AD in accordance with the applicable Bombardier repair drawings in Table 1 of this AD is acceptable for compliance with the requirements of this AD.
| Bombardier repair drawing | RD issue | Dated |
|---|---|---|
| RD 8/4-55-083 | 3 | April 16, 2003. |
| RD 8/4-55-084 | 1 | May 5, 2003. |
| RD 8/4-55-089 | 2 | June 6, 2003. |
| RD 8/4-55-090 | 8 | October 9, 2003. |
| RD 8/4-55-093 | 2 | June 20, 2003. |
| RD 8/4-55-094 | 4 | October 20, 2003. |
| RD 8/4-55-106 | 2 | July 31, 2003. |
| RD 8/4-55-110 | 3 | October 1, 2003. |
| RD 8/4-55-138 | 1 | October 29, 2003. |
(i) Within 4,000 flight hours after the effective date of this AD, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD in accordance with Part A of the service bulletin.
(1) Do a detailed inspection of the laminated shims for cracks, damage, or extrusion between the forward attachment fittings of the horizontal stabilizer and the top rib of the vertical stabilizer.
Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
(2) Do a breakaway torque check of the six attachment bolts in the attachment fittings of the front, middle, and rear spars.
If, during the inspection required by paragraph (i)(1) of this AD, any cracked, damaged, or extruded laminated shim is found, before further flight, replace the discrepant laminated shim with a solid shim, and replace the attachment bolts, barrel nuts, and retainers of both front spars with new parts, in accordance with Parts A and B of the service bulletin.
(k) If, during the torque check required by paragraph (i)(2) of this AD, any attachment bolt is found with a breakaway torque value outside the limits specified in the service bulletin, before further flight, replace the attachment bolt and its corresponding barrel nut and retainer with new parts, in accordance Part A of the service bulletin.
(1) Within 8,000 flight hours after the effective date of this AD, unless previously accomplished in accordance with paragraph (j) of this AD, replace the laminated shims, between the forward attachment fittings of the horizontal stabilizer and the top rib of the vertical stabilizer, with solid shims and replace the corresponding barrel nut and retainer with new parts, in accordance with Part B of the service bulletin.
Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement.
