AD 2001-13-18 Airworthiness Directives; Raytheon Aircraft Corporation Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes

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

(b) This AD applies to Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) airplanes, all serial numbers, that are certificated in any category.

(d) To address this problem, you must maintain the actions of AD 99-12-02 that are outlined in paragraphs (d)(1), (d)(2), and (d)(3) of this AD, including all subparagraphs, until you accomplish the initial inspection required in paragraph (d)(5) of this AD (paragraphs (d)(1) through (d)(4) are actions retained from AD 99-12-02, and paragraphs (d)(5) through (d)(7) are actions new to this AD):   Action When In accordance with (1) Accomplish the following placard requirements: All actions required prior to further flight after July 9, 1999 (the effective date of AD 99-12-02), unless already accomplished Not Applicable. (i) Fabricate two placards using letters of at least 1/10 -inch in height with each consisting of the following words: “Never exceed speed, Vne-175 MPH (152 knots) IAS; Normal Acceleration (G) Limits—0, and +2.5; ACROBATIC MANEUVERS PROHIBITED.” (ii) Install these placards on the airplane instrument panels (one on the front panel and one on the rear panel) next to the airspeed indicators within the pilot's clear view. (iii) Insert a copy of this AD into the Limitations Section of the Airplane Flight Manual (AFM). (2) Modify each airspeed indicator glass by accomplishing the following: All actions required within 10 hours time-in-service (TIS) after July 9, 1999 (the effective date of AD 99-12-02), unless already accomplished Not Applicable. (i) Place a red radial line on each indicator glass at 175 miles per hour (mph) (152 knots). (ii) Place a white slippage index mark between each airspeed indicator glass and case to visually verify that the glass has not rotated. (3) Mark the outside surface of the “g” meters with lines of approximately 1/16 -inch by 3/16 -inch, as follows: All actions required within 10 hours time-in-service (TIS) after July 9, 1999 (the effective date of AD 99-12-02), unless already accomplished Not Applicable. (i) A red line at 0 and 2.5; and (ii) A white slippage mark between each “g” meter glass and case to visually verify that the glass has not rotated. (4) The actions required by paragraphs (d)(1), (d)(2), and (d)(3) are no longer required after the initial inspection required in paragraph (d)(5) of this AD is accomplished Upon accomplishment of the initial inspection required in paragraph (d)(5) of this AD, unless already accomplished Raytheon Aircraft Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000. (5) Inspect the wing spar assemblies for cracks Initially inspect within the next 80 hours time-in-service (TIS) after August 16, 2001 (the effective date of AD 2001-13-18) or within 12 months after August 16, 2001 (the effective date of AD 2001-13-18), whichever occurs later, unless already accomplished. Inspect thereafter at intervals not to exceed 80 hours TIS Raytheon Aircraft Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000. (6) Replace any cracked wing spar assembly. A crack indication in the filler strip is allowed if the direction of the crack is toward the outside edge of the filler strip. If the direction of the crack is toward the inside edge of the filler strip or any crack is found in any other area, you must replace the cracked wing spar assembly Prior to further flight after the required inspection where the cracked wing spar assembly is found The applicable maintenance manual. (7) Submit a report to FAA that describes the damage found on the wing spar. Use the chart on pages 58 through 60 of Raytheon Aircraft Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000 Within 10 days after the initial inspection or within 10 days after August 16, 2001 (the effective date of AD 2001-13-18), whichever occurs later, unless already accomplished Pages 58 through 60 of Raytheon Aircraft Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000. (i) Submit this report even if no cracks are found. (ii) Submit this report to FAA at the address found in paragraph (g) of this AD.

(c) We are issuing this AD to detect and correct cracks in the wing spar assemblies and ensure the operational safety of the above-referenced airplanes.