AD 2006-18-51 Airworthiness Directives; Raytheon Aircraft Company Models 1900, 1900C, and 1900D Airplanes

Makes named: raytheon. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the following airplane models and serial numbers that are certificated in any category:   Models Serial Nos. (1) 1900 UA-3. (2) 1900C (C-12J) UB-1 through UB-74, UC-1 through UC-174, and UD-1 through UD-6. (3) 1900D UE-1 through UE-439.

To address this problem, you must do the following:   Actions Compliance Procedures (1) A one-time visual inspection of both the left and right wing rear spar lower caps for cracks and other damage such as loose or missing fasteners. At whichever occurs later after September 8, 2006 (the effective date of this AD), except to those who received emergency AD 2006-18-51, which contained the requirements of this amendment and became effective immediately upon receipt: (i) Within 24 hours; or (ii) Prior to further flight. Follow the procedures in the Appendix to this AD. (2) For the inspection in paragraph (e)(1) of this AD, you may return/position the airplane to a home base, hangar, maintenance facility, etc. For this repositioning, you may operate the airplane up to 3 hours time-in-service provided the flight(s) occur(s) no later than 30 days after September 8, 2006 (the effective date of this AD), except to those who received emergency AD 2006-18-51, which contained the requirements of this amendment and became effective immediately upon receipt. The following limitations are imposed for such a repositioning flight: (i) ONLY THE PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE OPERATION IS ALLOWED FOR THIS FLIGHT; (ii) FLIGHT INTO KNOWN OR FORECAST MODERATE OR SEVERE TURBULENCE IS PROHIBITED; and (iii) INDICATED AIRSPEED IS LIMITED TO 175 KNOTS MAXIMUM. (3) Repair any cracks or other damage such as loose or missing fasteners found during the inspection required in paragraph (e)(1) of this AD. Do this by obtaining and incorporating an FAA-approved repair scheme from RAC. Before further flight after the inspection required by paragraph (e)(1) of this AD. Contact RAC at Post Office Box 85, Wichita, Kansas 67201-0085; phone: 316-676-8366; fax: (316) 676-8745; e-mail: tom_peay@rac.ray.com. (4) Report the inspection results to the FAA and RAC. For the reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Within 72 hours after completing the inspection required in paragraph (e)(1) of this AD. Send your report to Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas 67209; fax: (316) 946-4107; e-mail: steven.potter@faa.gov; and Tom Peay, Raytheon Aircraft Company, Post Office Box 85, Wichita, Kansas 67201-0085; fax: (316) 676-8745; e-mail: tom_peay@rac.ray.com . Include in your report the following information: (i) Aircraft model and serial number; (ii) Number of cycles; (iii) Aircraft hours TIS; (iv) Left and right wing lower spar cap hours TIS; (v) Hours TIS on the spar cap since last inspection; (vi) Answer yes or no whether cracking, missing fasteners, or other damage was found; and (vii) If cracking was found, identify size and location of cracks. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4124; fax: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures in 14 CFR 39. APPENDIX TO AD 2006-18-51 Inspection Instructions—Raytheon Aircraft Company 1900 Series Wing Rear Spar Step 1. Lower the wing flaps to provide visual access to the wing rear spar cove area. Although the pictures show the flaps removed, this AD does not require flap removal to do the inspection. Step 2. Using a strong, high-intensity light visually inspect the area of the wing rear spar identified in Figure 1. There is ample visually visual access from above the upper surface of the flap. Look for cracks (like those shown in Figures 2 and 3) and loose or missing fasteners. Step 3. Clean the wing rear spar area 10 inches inboard and outboard of the buttock line (BL) 114 area. Step 4. Repeat the Step 2 inspection. BILLING CODE 4910-13-U ER08SE06.002 ER08SE06.003 ER08SE06.004 Issued in Kansas City, Missouri, on September 1, 2006. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-7511 Filed 9-7-06; 8:45 am] BILLING CODE 4910-13-C

This AD is the result of extensive cracks found in the wing rear spar lower caps and rear spar web of two of the affected airplanes. One of the airplanes also had missing fasteners. We are issuing this AD to detect and correct cracking and other damage in the wing rear spar lower caps of the affected airplanes before the cracks or damage lead to failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control.