Airworthiness Directive · Amendment 39-19877 · Fuselage
Bombardier, Inc., Airplanes
This AD applies to Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes, certificated in any category, serial numbers 9001 through 9844 inclusive, and 9998.
The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a report that cracking was discovered in a channel within a structural support member for the rudder quadrant, rudder feel unit assembly, and environmental control system due to fatigue. This AD requires repetitive inspections of the rudder quadrant box assembly for any cracking, and modification of the rudder quadrant box assembly. The FAA issuing this AD to address the unsafe condition on these products.
For airplanes that have accumulated fewer than 2,900 total flight cycles as of the effective date of this AD, and that have not been modified as specified in paragraph (i) of this AD: At the applicable time specified in paragraph (g)(1) or (2) of this AD, do a detailed visual inspection for cracking of the rudder quadrant box assembly, in accordance with paragraph 2.B. of the Accomplishment Instructions of the applicable service bulletin specified in figure 1 to paragraph (g) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles.
(1) For airplanes that have accumulated fewer than 2,000 total flight cycles as of the effective date of this AD: Inspect within 1,000 flight cycles after the effective date of this AD.
(2) For airplanes that have accumulated 2,000 total flight cycles or more, but fewer than 2,900 total flight cycles, as of the effective date of this AD: Inspect within 100 flight cycles after the effective date of this AD.
If any cracking is found during any inspection specified in paragraph (g) of this AD, do the actions specified in paragraph (i) of this AD at the applicable time specified in paragraphs (h)(1) through (4) of this AD.
(1) If any crack of 1.20 inch (30.48 mm) or longer is found on the forward (FWD) upper half rib: Do the actions within 100 flight cycles after discovery of the crack.
(2) If any crack of 0.40 inch (10.16 mm) or longer is found on the AFT lower half rib, do the actions within 100 flight cycles after discovery of the crack.
(3) If any crack is found on the left-hand (LH) channel that has grown from the air system's support fitting aft fastener hole to the adjacent air systems support fitting fastener hole (which is 0.625 inch (15.88 mm) from hole edge to hole edge) or longer, do the actions before further flight.
(4) If any crack is found on the LH channel that is less than 0.625 inch (15.88 mm) from hole edge to hole edge (which is the distance from the air system's support fitting aft fastener hole to the adjacent air system's support fitting fastener hole), do the actions within 50 flight cycles after discovery of the crack.
At the applicable time specified in paragraph (i)(1) or (2) of this AD, except as required by paragraph (h) of this AD: Modify the rudder quadrant box assembly. The modification includes surface and bolt-hole eddy current inspections for cracking of the left-hand channel; a detailed visual inspection for cracking of the forward and aft half ribs and bottom and top skins; applicable corrective actions; replacement of the rudder quadrant box half ribs, air systems support fitting, and LH channel; and installation of new rudder quadrant box back-up fittings. Do the modification and associated actions in accordance with paragraph 2.B., 2.C., and 2.D., of the Accomplishment Instructions of the applicable service bulletin specified in figure 2 to paragraph (i) of this AD; except, where the applicable service bulletin specifies to contact Bombardier for appropriate action, corrective actions must be done before further flight in accordance with the procedures specified in paragraph (l)(2) of this AD.
(1) For airplanes that have accumulated 2,900 total flight cycles or fewer as of the effective date of this AD, do the required actions before the accumulation of 3,000 total flight cycles, or within 60 months after the effective date of this AD, whichever occurs first.
(2) For airplanes that have accumulated more than 2,900 total flight cycles as of the effective date of this AD, do the required actions within 100 flight cycles or 12 months, whichever occurs first, after the effective date of this AD.
Airplanes that have been modified as specified by any modification identified in paragraphs (j)(1) through (4) of this AD (which are not required by this AD), meet the requirements specified in paragraph (i) of this AD.
(1) Bombardier Repair Modification R700T400669, Revision C, dated January 19, 2018, or Bombardier Repair Modification R700T400669, Revision G, dated May 30, 2018.
(2) Bombardier In-Service Modification IS700-53-0024, Revision A, dated July 24, 2018.
(3) Bombardier Service Request for Product Support Action (SRPSA) 000220372.
(4) Bombardier Service Request for Product Support Action (SRPSA) 000271526.
Accomplishing the actions in paragraph (i) or (j) of this AD terminates all of the requirements in paragraph (g) of this AD.
