Airworthiness Directive · Amendment 39-16933 · Stabilizers
CPAC, Inc. Airplanes
This AD applies to CPAC, Inc. (type certificate formerly held by Commander Aircraft Corporation, Gulfstream Aerospace Corporation, and Rockwell International) Models 112, 112B, 112TC, 112TCA, 114, 114A, 114B, and 114TC airplanes, all serial numbers, certificated in any category. Type Certificate No. A12SO does not include Models 112A and 115. The Model 112A is a Rockwell “marketing name” for the Model 112. The Model 115 is a Rockwell “marketing name” for the Model 114. Since they are type-certificated as Model 112 and Model 114, this AD is applicable to the Models 112A and 115.
We are superseding an existing airworthiness directive (AD) for all CPAC, Inc. (type certificate formerly held by Commander Aircraft Corporation, Gulfstream Aerospace Corporation, and Rockwell International) Models 112, 112B, 112TC, 112TCA, 114, 114A, 114B, and 114TC airplanes. That AD currently requires a one-time inspection of the elevator spar for cracks and, if any crack is found, either replace with a serviceable elevator spar that is found free of cracks or repair/modify the elevator spar with an FAA-approved method. That AD also requires reporting to the FAA the results of the inspection. Since we issued that AD, using the data collected through the reporting requirement, we have determined there is a need for continued inspections. This new AD requires repetitive inspections of the elevator spar for cracks and, if any crack is found, either replacing with a serviceable elevator spar that is free of any cracks and/or corrosion or repairing/modifying the elevator spar with an FAA-approved procedure. We are issuing this AD to correct the unsafe condition on these products.
Within the next 5 hours time-in-service (TIS) after April 4, 2011 (the effective date retained from AD 2011-07-13 (76 FR 18376, April 4, 2011)), visually inspect the left-hand (LH) and right-hand (RH) elevator spar behind and around the outboard hinge bracket on the elevator spar for cracks. Do the inspection following the procedures specified in paragraph (j) of this AD. If cracks are found during this inspection, take the necessary corrective actions specified in paragraph (k) of this AD.
Within 30 days after the inspection required in paragraph (g) of this AD, report the results of the inspection to the FAA, Wichita Aircraft Certification Office (ACO), Attn: T.N. Baktha, Senior Aerospace Engineer, 1801 Airport Road, Room 100; Wichita, Kansas 67209; phone: (316) 946-4155; fax: (316) 946-4107; email: t.n.baktha@faa.gov. Include the following information:
(1) Airplane model and serial number.
(2) Hours TIS at time of inspection.
(3) Annotate any cracking found, including the exact location and length of any cracks.
(4) Any installations, repairs, modifications, etc. that have been done on your airplane in the elevator spar area or that could have affected the elevator spar.
(5) Type of operation primarily flown.
As a result of the inspection required in paragraph (g) of this AD, if the elevator spar was:
(1) Replaced with a new elevator spar, within the next 300 hours TIS after the replacement, visually inspect the elevator spar behind the outboard hinge bracket and surrounding area for cracks. Repetitively inspect thereafter at intervals not to exceed 12 months or 150 hours TIS, whichever occurs first. Do the inspection following the procedures specified in paragraph (j) of this AD.
(2) Replaced with a serviceable elevator spar (one that was in service before and had no cracks and/or corrosion), within the next 150 hours TIS after the replacement, visually inspect the elevator spar behind the outboard hinge bracket and surrounding area for cracks. Repetitively inspect thereafter at intervals not to exceed 12 months or 150 hours TIS, whichever occurs first. Do the inspection following the procedures specified in paragraph (j) of this AD.
(3) Found free of cracks, within the next 150 hours TIS after the inspection, visually inspect the elevator spar behind the outboard hinge bracket and surrounding area for cracks. Repetitively inspect thereafter at intervals not to exceed 12 months or 150 hours TIS, whichever occurs first. Do the inspection following the procedures specified in paragraph (j) of this AD.
(1) Disconnect the elevator trim pushrod at the trim tab.
(2) Remove the hinge bolts at the horizontal stabilizer points.
(3) Remove six screws and two bolts at the inboard end of the elevator and remove the elevator.
(4) Remove all fasteners common to the elevator outboard aft end rib, part number (P/N) 44330, and elevator skin, P/N 44323.
(5) Remove the remaining two fasteners common to the elevator outboard aft end rib (P/N 44330) and the elevator spar, P/N 44211.
(6) Remove the elevator aft end rib, P/N 44330, to gain access to the aft side of the elevator spar.
(7) Remove the four bolts, washers, and nuts that secure the outboard elevator hinge bracket, P/N 44285.
(8) Remove elevator hinge bracket, P/N 44285, from the elevator spar.
(9) Clean in and around the location of the elevator outboard hinge bracket, outboard elevator hinge, and the outboard elevator hinge bracket (as applicable) on the elevator spar and visually inspect for cracks. Use a 10× magnifier to facilitate the detection of any crack.
(1) If cracks are found during any inspection required in paragraphs (g), (i)(1), (i)(2), or (i)(3) of this AD, before further flight, either replace the elevator spar with a new spar or a serviceable spar that is found free of cracks and/or corrosion or repair/modify the elevator spar following a procedure approved for this AD by the FAA, Wichita ACO;
(2) After doing the actions required in paragraph (k)(1) of this AD, before further flight, reassemble the elevator assembly, rebalance the elevator, and reinstall on the airplane following standard repair practices. Ensure elevator rigging is within tolerance, and that the system operates with ease, smoothness, and positiveness appropriate to its function; and
(3) After taking corrective action, continue with the repetitive inspections required in paragraphs (i)(1), (i)(2), and (i)(3) of this AD.
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.
