AD 2005-01-18 Airworthiness Directives; Raytheon Aircraft Company Beech 100, 200, and 300 Series Airplanes

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

(c) This AD affects the following Beech airplane models and serial numbers that are certificated in any category:   Model Serial Nos. (1) A100-1 (U-21J) BB-3 through BB-5 (2) 200 and B200 BB-2 and BB-6 through BB-1462. (3) A200 (C-12A) and A200 (C-12C) BC-1 through BC-75 and BD-1 through BD-30. (4) A200C (UC-12B) BJ-1 through BJ-66. (5) A200CT (C-12D). BP-1, BP-22, and BP-24 through BP-51. (6) A200CT (FWC-12D) BP-7 through BP-11. (7) A200CT (RC-12D) GR-1 through GR-13. (8) A200CT (C-12F) BP-52 through BP-63. (9) A200CT (RC-12G) FC-1 and FC-3. (10) A200CT (RC-12H) GR-14 through GR-19. (11) A200CT (RC-12K) FE-1 through FE-9. (12) A200CT (RC-12P) FE-10 through FE-24. (13) A200CT (RC-12K) FE-25 through FE-31. (14) 200C and B200C BL-1 through BL-72 and BL-124 through BL-138. (15) 200CT BN-1 through BN-4 and B200CT. (16) 200T BT-1 through BT-38 and B200T. (17) B200C (C-12F) BL-73 through BL-112 and BL-118 through BL-123. (18) B200C (C-12F) BP-64 through BP-71. (19) B200C (UC-12F) BU-1 through BU-10. (20) B200C (UC-12M) BV-1 through BV-12. (21) B200CT FG-1 and FG-2. (22) 300 FA-1 through FA-228. (23) 300 FF-1 through FF-19. (24) B300 FL-1 through FL-103. (25) B300C FM-1 through FM-8. (26) B300C FN-1.

(e) To address this problem, you must do the following:   Actions Compliance Procedures (1) For airplanes that have been known cracks that exist in any of the aft fuselage stringer locations (No. 5 through No. 11 on both the left-hand and right-hand sides). Either modify or incorporate repairs as specified below. These cracks could have been detected through compliance with AD 93-25-07 and/or Raytheon Mandatory Service Bulletin SB 53-2472, any revision level: (i) Incorporate the applicable modification kit or kits as specified in Raytheon Mandatory Service Bulletin SB 53-2472, Rev. 4, Issued: June, 1993, Revised: July, 2003; or (ii) Incorporate external doubler repairs on all aft fuselage stringer locations (No. 5 through No. 11 on both the left-hand and right-hand sides) If airplane has less than five known cracked stringers: Within 25 cycles after March 1, 2005 (the effective date of this AD), unless already done. If cycles are unknown, then you may divide hours time-in-service (TIS) by .75 (18.75 hours TIS ÷ .75 = 25 cycles). If airplane has five or more known cracked stringers: Before further flight after March 1, 2005 (the effective date of this AD), unless already done. AD 93-35-07 already required this. Incorporate the modification kit(s) following the procedures in Raytheon Mandatory Service Bulletin SB 53-2472, Rev. 4, Issued: June, 1993, Revised: July, 2003. Incorporate the external doubler repairs following the procedures in the maintenance manual. (2) For all airplanes that do not have either the modifications or repairs specified in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD incorporated in all aft fuselage stringer locations (No. 5 through No. 11 on both the left-hand and right-hand sides): Inspect these aft fuselage stringers. If sealant covers the stringers, you must remove it to facilitate the required inspections and then reapplied. You may terminate the repetitive inspections when all aft fuselage stringer locations (No. 5 through No. 11 on both the left-hand and right-hand sides) are modified. For airplanes affected by AD 93-25-07: Initially inspect at the next inspection interval required by AD 93-35-07. Repetitively inspect thereafter at intervals not to exceed 500 cycles. If cycles are unknown, then you may divide TIS by .75 (375 hours TIS ÷ .75 = 500 cycles). For airplanes not affected by AD 93-25-0-7: Initially inspect upon accumulating 2,500 cycles on the fuselage or within the next 25 cycles after March 1, 2005 (the effective date of this AD), whichever occurs later, unless already done. Repetitively inspect thereafter at intervals not to exceed 500 cycles. If cycles are unknown, then you may divide hours TIS by .75 (1,875 hours TIS ÷ .75 = 2,500 cycles; 375 hours TIS ÷ .75 = 500 cycles; and 18.75 hours TIS ÷ .75 = 25 cycles) Inspect following the procedures in Raytheon Mandatory Service Bulletin SB 53-2472. Rev. 4, Issued: June, 1993, Revised: July, 2003. (3) If any cracks are found during any inspection required by this AD, do one of the following: (i) Incorporate the applicable modification kit or kits as specified in Raytheon Mandatory Service Bulletin SB 53-2472, Rev. 4, Issued: June, 1993, Revised: July, 2003; or (ii) Incorporate external doubler repairs on all aft fuselage stringer locations (No. 5 through No. 22 on both the left-hand and right-hand sides) If less than five cracked stringers are found: Within 25 cycles after March 1, 2005 (the effective date of this AD), unless already done. If cycles are unknown, then you may divide hours TIS by .75 (18.75 hours TIS ÷ .75 = 25 cycles). If five or more cracked stringers are found: Before further flight after any inspection where five cracked stringers are found, unless already done Incorporate the modification kit(s) following the procedures in Raytheon Mandatory Service Bulletin SB 53-2472, Rev. 4, Issued: June, 1993, Revised: July, 2003. Incorporate the external doubler repairs following the procedures in the maintenance manual.

(d) As currently written, AD 93-25-07 allows continued flight if cracks are found in less than five fuselage stringers in the area of the rear pressure bulkhead. In 1996, FAA developed policy to not allow airplane operation when known cracks exist in primary structure, unless the ability to sustain limit and ultimate load with these cracks is proven. The fuselage stringers in the area of the rear pressure bulkhead are considered primary structure. This AD will bring the actions of AD 93-25-07 in compliance with current FAA policy. The actions specified in this AD are intended to detect and correct any cracked fuselage stringers in the rear pressure bulkhead area, which could result in structural damage to the fuselage. This damage could lead to failure of the fuselage with potential loss of control of the airplane.

(b) This AD supersedes AD 93-25-07, Amendment 39-8773.