94-20-04 R1: V-tail

94-20-04 R1 Raytheon Aircraft Company (Beech Aircraft Corporation formerly held Type Certificate (TC) No. A-777 and TC No. 3A15): Amendment 39-12919; Docket No. 93-CE-37-AD; Revises AD 94-20-04, Amendment 39-9032. (a) What airplanes are affected by this AD? This AD affects the following airplanes that are certificated in any category: (1) Beech Models C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, and P35 airplanes, all serial numbers; and (2) Beech Models S35, V35, V35A, and V35B airplanes, all serial numbers, that do not have the straight tail conversion modification incorporated in accordance with Supplemental Type Certificate (STC) SA2149CE. Note 1: Beech Models 35, 35R, A35, B35 airplanes were included in the Applicability of AD 94-20-04 . We have removed Beech Models 35, 35R, A35, and B35 airplanes from the Applicability section of this AD and incorporated the actions applicable to these airplanes into another AD action. Part of this other AD action is the incorporation of Raytheon Service Raytheon Service Bulletin 27-3358. (b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes identified in paragraphs (a), (a)(1), and (a)(2) of this AD must comply with this AD. (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. (d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following: Actions Compliance Procedures (1) Verify that the ruddervator balance is within the manufacturer s specified limits as defined in the applicable shop or maintenance manual and balance the ruddervator control surfaces, as necessary Within the next 100 hours TIS after November 28, 1994 (the effective date of AD 94-20-04) and thereafter prior to further flight after the ruddervators are repaired or repainted (even if stripes are added or paint is touched up) Verify in accordance with the applicable shop or maintenance manual. Balance the ruddervator control surfaces in accordance with Section 3 of Beech Shop Manual 35-590096B19, or subsequent revisions. (2) Visually inspect the empennage, aft fuselage, and ruddervator control system for damage (i) Repair or replace any damaged parts; and (ii) Set the elevator controls, rudder and tab system controls, cable tensions, and rigging Inspect and set the controls, tension, and rigging within the next 100 hours TIS after November 28, 1994 (the effective date of AD 94-20-04) and thereafter at intervals not to exceed 100 hours TIS. Accomplish any repairs and replacements prior to further flight after the applicable inspection In accordance with the procedures and as specified in the instructions to Beech Kit 35-4017-1 "Kit Information Empennage and Aft Fuselage Inspection", as specified in Beech Service Bulletin No. 2188, dated May, 1987. (3) Removeall external stabilizer reinforcements installed during incorporation of either Supplemental Type Certificate (STC) SA845GL, STC SA846GL, STC SA1650CE, STC SA2286NM, or STC SA2287NM, as applicable (i) Seal or fill any residual holes with appropriate size rivets (ii) The internal stub spar incorporated through STC SA1649CE and STC SA1650CE may be retained (iii) The external angles incorporated through STC SA1649CE may also be retained by properly trimming the leading edges section to permit installation of the stabilizer reinforcement referenced in paragraph (d)(4)(i) of this AD (iv) For the Beech Models S35, V35, V35A, and V35B airplanes, you may retain and use the tail-safe external angles that were installed in accordance with STC SA1649CE instead of the stabilizer reinforcement specified in paragraph (d)(4)(i) of this AD. Within the next 100 hours TIS after November 28, 1994 (the effective date of AD 94-20-04), unless already accomplished In accordance with the applicable maintenance information. (4) Accomplish the following: (i) Install stabilizer reinforcements; (ii) Set the elevator nose-down trim; and (iii) Replace the ruddervator tab control cables with larger diameter cables Within the next 100 hours TIS after November 28, 1994 (the effective date of AD 94-20-04), unless already accomplished In accordance with the instructions to RAC Kit No. 35-4016-3, 35-4016-5, 35-4016-7, or 35-4016-9, as applicable and as specified in Beech SB No. 2188, dated May, 1987. (5) Verify the accuracy of the airplane basic weight and balance information and correct any discrepancies Accomplish the airplane basic weight and balance accuracy verification within the next 100 hours TIS after November 28, 1994 (the effective date of AD 94-20-04), unless already accomplished. Correct any discrepancies prior to further flight after the verification Use the procedures contained in the Appendix to this AD. (e) Can I comply with this AD in any other way? (1) You may use an alternative method of compliance or adjust the compliance time if: (i) Your alternative method of compliance provides an equivalent level of safety; and (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. (2) Alternative methods of compliance approved in accordance with AD 94-20-04, which is revised by this AD, are approved as alternative methods of compliance with this AD. Note 2: This AD applies to each airplane identified in paragraphs (a), (a)(1), and (a)(2) 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 (e) 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. (f) 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, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4155; facsimile: (316) 946-4407. (g) 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 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. (h) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with Beech Kit No. 35-4016-3, 35-4016-5, 35-4016-7, or 35-4016-9, and the instructions to Beech Kit 35-4017-1 "Kit Information Empennage & Aft Fuselage Inspection", as applicable and specified in Beech Service Bulletin No. 2188, dated May 1987. The Director of the Federal Register previously approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51 as of November 28, 1994 (59 FR 49785, September 30, 1994). You may get copies from the Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201-0085. You may view copies at 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. (i) Does this AD action affect any existing AD actions? This amendment revises AD 94-20-04, Amendment 39-9032. (j) When does this amendment become effective? This amendment becomes effective on December 10, 2002. Appendix to AD 94-20-04 R1 Weight and Balance Accuracy Method No. 1 1. Review existing weight and balance documentation to assure completeness and accuracy of the documentation from the most recent FAA-approved weighing or from factory delivery to date of compliance with this AD. 2. Compare the actual configuration of the airplane to the configuration described in the weight and balance documentation. 3. 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. Weight and Balance Information Accuracy Method No. 2 1. 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). 2. 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.