AD 2011-07-13 Airworthiness Directives; 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

Makes named: commander. Models named: 112, 112B, 112TC, 112TCA, 114, 114A, 114B, 114TC. Read the applicability below — it usually turns on serial or part numbers too.

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.

Comply with this AD within the compliance times specified. Inspection/Repair (g) Within the next 5 hours time-in-service after the effective date of this AD, do the following for the left-hand and right-hand elevators: (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, P/N 44285. (8) Remove elevator hinge, P/N 44285, from the elevator spar. (9) Clean in and around the location of the outboard bracket on the elevator spar and visually inspect for cracks. Use a 10X magnifier to facilitate the detection of any crack. (10) If cracks are found, before further flight, do the following: (i) Either replace the elevator spar with a serviceable spar that is found free of cracks or repair/modify the elevator spar following a procedure approved for this AD by the FAA, Wichita Aircraft Certification Office (ACO); and (ii) 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. Note: Elevator rigging and rebalancing, torque values, and other general maintenance information can be found in the maintenance manual. Reporting Requirement (h) Report the results of the inspection to the FAA, Wichita ACO, FAA, Attn: T.N. Baktha, Senior Aerospace Engineer, 1801 Airport Road, Room 100; phone: (316) 946-4155; fax: (316) 946-4107; e-mail: t.n.baktha@faa.gov. Include the following information: (1) Airplane model and serial number. (2) Hours time-in-service 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 in. Paperwork Reduction Act Burden Statement (i) A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Wichita 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. Related Information (k) For more information about this AD, contact T.N. Baktha, Senior Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100; phone: (316) 946-4186; fax: (316) 946-4107; e-mail: t.n.baktha@faa.gov. Issued in Kansas City, Missouri, on March 28, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011-7729 Filed 4-1-11; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports of a total of nine elevator spar cracks across seven of the affected airplanes, including a crack of 2.35 inches just below the outboard hinge of the right-hand elevator. We are issuing this AD to prevent structural failure of the elevator spar due to such cracking, which could result in separation of the elevator from the airplane with consequent loss of control.