2002-21-13: V-tail

2002-21-13 Raytheon Aircraft Company (Beech Aircraft Corporation formerly held Type Certificate (TC) No. A-777): Amendment 39-12920; Docket No. 2000-CE-44-AD; Supersedes AD 98-13-02, Amendment 39- 10590. \n\n\t(a) What airplanes are affected by this AD? This AD affects Beech Models 35, 35R, A35, and B35 airplanes, all serial numbers, that are certificated in any category. \n\n\t(b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes referenced in paragraph (a) of this AD must comply with this AD. \n\n\t(c) What problem does this AD address? The actions specified by this AD are intended to prevent structural failure of the V-tail, which could result in loss of control of the airplane. \n\n\tNote 1: Only the inspections, repairs, replacements, and airplane basic weight and balancing requirements as specified in this AD are required by paragraphs (d)(5), (d)(6), (d)(7), (d)(7)(i), (d)(7)(ii) of this AD and the Appendix to this AD. Other actions specified in Raytheon Service Bulletin SB 27-3358 such as a DER review for major structural modifications are not required by this AD. If you have major modifications incorporated in the aft fuselage or empennage, we recommend a Structures DER review to ensure structural integrity is maintained after the modifications. \n\n\t(d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following: \n\n\n\nActions\nCompliance\nProcedures\n(1) Fabricate a placard that restricts the never exceed speed (Vne) to no more than 144 miles per hour (MPH) or 125 knots (KTS) indicated airspeed (IAS), and install this placard on the instrument panel within the pilot's clear view. The placard should utilize letters of at least 0.10-inch in height and contain the following words: ??Never exceed speed, Vne, 144 MPH (125 KTS) IAS''.\nWithin the next 10 hours time-in-service (TIS) after July 7, 1998 (the effective date of AD 98-13-02), unless already accomplished.\nNot Applicable.\n(2) Mark a red line on the airspeed indicator glass at 144 MPH (125 KTS) and mark a white slippage mark on the outside surface of the airspeed indicator between the glass and case.\nWithin the next 10 hours time-in-service (TIS) after July 7, 1998 (the effective date of AD 98-13-02), unless already accomplished.\nNot Applicable.\n(3) Insert a copy of this AD into the Limitations Section of the airplane flight manual (AFM).\nWithin the next 10 hours time-in-service (TIS) after July 7, 1998 (the effective date of AD 98-13-02), unless already accomplished.\nNot Applicable.\n(4) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may fabricate and install the placard as required by paragraph (d)(1) of this AD and insert this AD into the Limitations Section of the AFM as required by paragraph (d)(3) of this AD.\nWithin the next 10 hours time-in-service (TIS) after July 7, 1998 (the effectivedate of AD 98-13-02), unless already accomplished.\nMake an entry into the aircraft records showing compliance with this AD in accordance with 43.9 of the Federal Aviation Regulations (14 CFR 43.9).\n(5) Visually inspect the empennage, aft fuselage, and ruddervator control system for damage:\n(i) Part of this is an inspection of the aft fuselage skin for wrinkles or cracks. Specific skin thicknesses are presented in Figures 1 and 2 of this AD. The skin thickness measurement is not repetitive.\n(ii) The inspection and setting of the travels on the elevator and elevator trim tabs are not repetitive.\n(iii) Repair or replace any damaged parts and set the elevator controls, rudder and tab system controls, cable tensions, and rigging.\nInspect within the next 100 hours TIS after the last inspection required by AD 94-20-04 or within the next 25 hours TIS after December 10, 2002 (the effective date of this AD), whichever occurs later, and thereafter at intervals not to exceed 100 hours TIS, except for the skin thickness measurement and the inspection and setting of the travels on the elevator and elevator trim tabs, which are one-time actions. Accomplish any repairs, replacements, and adjustments prior to further flight after the applicable inspection.\nAccomplish the inspection and repairs or replacements in accordance with the procedures in paragraphs (5)(a) through (5)(f) of the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon Service Bulletin No. SB 27-3358, Issued: February, 2000, and use a digital ultrasonic skin tester or equivalent skin tester or direct methods that utilize calipers and micrometers. Specific skin thicknesses are contained in Figures 1 and 2 of this AD.\n(6) Verify the accuracy of the airplane basic weight and balance information and correct any discrepancies.\nAccomplish the airplane basic weight and balance accuracy verification within the next 100 hours TIS after December 10, 2002 (the effective date of this AD), unless already accomplished as previously required by AD 94-20-04. Correct any discrepancies prior to further flight after the verification.\nUse the procedures contained in the Appendix to this AD.\n(7) Inspect the aft fuselage, ruddervator, and related systems for acceptable condition:\n(i) Repair or replace any parts found unacceptable as specified in the service bulletin.\n(ii) Rebalance the ruddervators to the new specifications that reduce the upper limit from 19.8 to 18 inch-pounds (tail heavy). This is not necessary initially if you can positively verify in the logbook that the ruddervators meet the limits specified in the service bulletin:\n(A) To positively show this, the entry must indicate that the ruddervator is within the specified limits and list the details of the balancing.\n(B) This must include the balancing methods used and the amount of weights and washers used.\n(iii) Discontinue the placard and operating limitations required by paragraphs (d)(1) through (d)(4) of this AD.\nAccomplish the inspections within the next 3 years after December 10, 2002 (the effective date of this AD), unless already accomplished. Accomplish any repair or replacement prior to further flight after the inspection. Accomplish any ruddervator rebalancing prior to further flight after the inspection, unless previously accomplished within the last 100 hours TIS, and thereafter when the ruddervators are repaired or repainted (even if stripes are added or paint is touched up).\nAccomplish the inspection and repairs or replacements in accordance with the procedures in the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon Service Bulletin No. SB 27-3358, Issued: February, 2000. Accomplish the rebalancing in accordance with Section 3A(8) of the service bulletin and use the procedure in Section 3 of Beech Shop Manual 35-590096B19 (or subsequent revision).\n\n\t(e) Where can I find Figures 1 and 2 of this AD? Figures 1 and 2 of this AD, as referenced in paragraph (d)(5)(i) of this AD, follow: \n\n\n\n\n\n\t(f) Can Icomply with this AD in any other way? (1) You may use an alternative method of compliance or adjust the compliance time if: \n\n\t(i) Your alternative method of compliance provides an equivalent level of safety; and \n\n\t(ii) The Manager, Wichita Aircraft Certification Office (ACO), approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. \n\n\t(2) Alternative methods of compliance approved in accordance with AD 98-13-02, which is superseded by this AD, are approved as alternative methods of compliance for the corresponding portion of this AD. \n\n\tNote 2: This AD applies to each airplane identified in paragraph (a) of this AD, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/ operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if you have not eliminated the unsafe condition, specific actions you propose to address it. \n\n\t(g) Where can I get information about any already-approved alternative methods of compliance? Contact Mr. T.N. Baktha, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946- 4155; facsimile: (316) 946-4407. \n\n\t(h) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD. \n\n\t(i) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with Raytheon Service Bulletin SB 27-3358, Issued: February, 2000. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You can get copies from Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201-0085. You can look at copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. \n\n\t(j) Does this AD action affect any existing AD actions? This amendment supersedes AD 98-13-02, Amendment 39-10590. \n\t(k) When does this amendment become effective? This amendment becomes effective on December 10, 2002. \n\nAppendix to AD 2002-21-13 \n\nWeight and Balance Accuracy Method No. 1 \n\n\t1. Review existing weight and balance documentation to assure completeness and accuracy of thedocumentation from the most recent FAA-approved weighing or from factory delivery to date of compliance with this AD. \n\n\t2. Compare the actual configuration of the airplane to the configuration described in the weight and balance documentation. \n\n\t3. If equipment additions or deletions are not reflected in the documentation or if modifications affecting the location of the center of gravity (e.g., paint or structural repairs) are not documented, determine the accuracy of the airplane weight and balance data in accordance with Method No. 2. \n\nWeight and Balance Information Accuracy Method No. 2 \n\n\t1. Determine the basic empty weight and center of gravity (CG) of the empty airplane using the Weighing Instructions in the Weight and Balance section of the airplane flight manual/pilot's operating handbook (AFM/POH). \n\n\t2. Record the results in the airplane records, and use these new values as the basis for computing the weight and CG information as specified in the Weight and Balances section of the AFM/POH.