2007-06-01: Front and rear horizontal stabilizer spars

2007-06-01 Raytheon Aircraft Company: Amendment 39-14982; Docket No. FAA-2006-25105; Directorate Identifier 2006-CE-33-AD. \n\nEffective Date \n\n\t(a) This AD becomes effective on April 16, 2007. \n\nAffected ADs \n\n\t(b) This AD supersedes AD 62-24-01, Amendment 39-508. \n\nApplicability \n\n\t(c) This AD affects the following airplane models and serial numbers that are certificated in any category: \n\n\nModel\nSerial numbers\nBeech 45 (YT-34)\nAll\nBeech A45 (T34A, B-45)\nAll\nBeech D45 (T-34B)\nAll\n\nUnsafe Condition \n\n\t(d) This AD results from our determination that the surface eddy current inspection method should be used in place of the dye penetrant inspection method currently required in AD 62-24-01. We are issuing this AD to prevent failure of the front and/or rear horizontal stabilizer spars caused by fatigue cracks. This failure could result in stabilizer separation and loss of control of the airplane. \n\nCompliance \n\n\t(e) Using the surface eddy current inspection procedures outlined in the appendix of this AD, inspect the front and rear horizontal stabilizer spars between the butt rib and the inboard end for cracks, unless already done, as follows: \n\n\t(1) If the last inspection of the front and rear horizontal stabilizer spars was done using the surface eddy current method (or FAA-approved equivalent method) to show compliance with AD 62-24-01 and/or to show compliance with the alternative method of compliance (AMOC) to AD 2004-25-51: Repetitively inspect thereafter at intervals not to exceed 500 hours time-in-service (TIS). \n\n\t(2) If the last inspection of the front and rear horizontal stabilizer spars required by AD 62-24-01 was done using the dye penetrant method: Inspect initially as presented in the table below and repetitively thereafter at intervals not to exceed 500 hours TIS: \n\n\nIf\nThen\n(i) Less than 200 hours TIS have passed since the last inspection required by AD 62-24-01:\nInspect at whichever of the following occurs later:(A) Upon accumulating 200 hours TIS since the last inspection required by AD 62-24-01; or \n(B) Within the next 6 months after April 16, 2007 (the effective date of this AD).\n(ii) If 200 hours TIS or more have passed since the last inspection required by AD 62-24-01:\nInspect at whichever of the following occurs first, unless paragraph (e)(2)(iii) of this AD applies, as specified below:\n(A) At the next repetitive inspection required by AD 62-24-01; or\n(B) Within the next 6 months after April 16, 2007 (the effective date of this AD).\n(iii) If paragraph (e)(2)(ii) results in the initial surface eddy current inspection becoming mandatory within 30 days after the effective date of this AD:\nInspect within the next 30 days after April 16, 2007 (the effective date of this AD).\n\n\nAlternative Methods of Compliance (AMOCs) \n\n\t(f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: T.N. Baktha, Aerospace Engineer, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4155; fax: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. \n\n\t(g) AMOCs approved for AD 62-24-01 are approved for this AD. \n\nAppendix to AD 2007-06-01 \n\nSurface Eddy Current Inspection Procedure \n\n\tNote: This surface eddy current inspection procedure is based on T-34 Spar Corporation TSC 3506, Rev C, dated May 10, 2005. The T-34 Spar Corporation is allowing the use of this procedure to be included in this Airworthiness Directive. Alternative methods of compliance procedures will be allowed, if approved by the Wichita Aircraft Certification Office and requested using the procedures found in 14 CFR 39.19. \n\n\tPurpose: This procedure is to be used to detect cracks in the inner and outer spars of the front and rear spar assemblies of Raytheon Aircraft Company Beech Models 45 (YT-34), A45 (T-34A, B- 45), and D45 (T-34B) airplane stabilizers outside of the steel bushings in the attach holes. \n\n\tArea To Be Inspected: To access the area of inspection, remove the stabilizer from the airplane. The areas to be inspected include the forward and aft surfaces of the inner and outer front and rear spars of the horizontal stabilizers in the areas surrounding each of the attach holes. \n\n\tPreparing the Area for Inspection: Thoroughly clean area to be inspected with solvent (acetone or equivalent) as required until no signs of dirt, grime, or oil remain on the front and rear spars from the closeout former inboard on the forward and aft surfaces of the spars. \n\n\tSurfaces to be inspected should be smooth and corrosion-free. Any loss of thickness due to corrosion below material thickness tolerance is cause for rejection of the structure. An ultrasonic tester may be used to determine if material thickness has been compromised. \n\n\tEquipment Requirements: Nortec Stavely 2000D Eddy Current Tester or equivalent. \n\n\tProbe: 50-500 KHz, shielded, absolute, 0.071'' diameter (0.090max. diameter), right angle, pencil style, surface probe, 5 long, \1/2\'' drop or equivalent. Use 0.025'' notch (beyond head) for calibration \n\n\tPersonal Requirements: Technicians with Eddy Current, Level II or Level III per one of the following specifications: ATA specification 105, SNT-TC-1A, or NAS-410 (MIL-std 410E). \n\n\tMethods: Typical Set-up Parameters: \n\n\tFrequency-350 KHz, Gain Vertical-75 dB, Horizontal-69 dB, Drive- Mid, Filters- Lo Pass-30, Hi Pass-0, Lift off-Horizontal to the left, adjust as required. The most reliable indication (minimum of 1\1/2\ to 2 graticules) of the smallest observable flaw in the coupon (see the attached Figures) occurs from the notch extending 0.025'' past the edge of the nominal fastener head (total notch length of 0.100'' from the edge of the nominal hole). Install appropriate aluminum guide pin into bushing such that the edge of the guide pin is flush with the edge of the bushing. Using the pin (see the attached Figures) as a guide, circlethe area surrounding the steel bushing with the probe and adjacent area (approximately \1/4\'') to inspect for cracks. Inspect forward and aft surfaces surrounding bushings of each spar. \n\n\tNote: T-34 Spar Corporation, 2800 Airport Road, Hanger A, Ada, Oklahoma, 74820 is a source for these coupons and pin. \n\n\tAccept/Reject Criteria: Any repeatable flaw indication is cause for rejection in accordance with the procedure. In the event that any crack is detected, describe the flaw in detail providing sketch as needed and send the information to the Wichita ACO. \n\n\tDocumentation Requirements: Record inspection findings in the aircraft logbook. \n\n\n\n\n\n\n\n Figure 2\n\n\n\nFigure 3\n\n\n\nFigure 4\n\n\n\nFigure 5