Airworthiness directives › 2004-17-02
AD 2004-17-02 Airworthiness Directives; Raytheon Aircraft Company 65, 90, 99, 100, 200, 300, and 1900 Series Airplanes
Makes named: raytheon. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model Serial Nos. (1) 65-A90, B90, C90, and C90A LJ-76, LJ-114 through LJ-1691. (2) E90 LW-1 through LW-347. (3) F90 LA-2 through LA-236. (4) 99, 99A, A99A, B99 and C99 U-1 through U-239. (5) 100 and A100 B-1 through B-94, B-100 through B-204, and B-206 through B-247. (6) B100 BE-1 through BE-137. (7) 200 and B200 BB-2, BB-6 through BB-185, BB-187 through BB-202, BB-204 through BB-269, BB-271 through BB-407, BB-409 through BB-468, BB-470 through BB-488, BB-490 through BB-509, BB-511 through BB-529, BB-531 through BB-550, BB-552 through BB-562, BB-564 through BB-572, BB-574 through BB-590, BB-592 through BB-608, BB-610 through BB-626, BB-628 through BB-646, BB-648 through BB-664, BB-666 through BB-694, BB-696 through BB-797, BB-799 through BB-822, BB-824 through BB-870, BB-872 through BB-894,BB-896 through BB-990, BB-992 through BB-1051, BB-1053 through BB-1092, BB-1094, BB-1095, BB-1099 through BB-1104, BB-1106 through BB-1116, BB-1118 through BB-1184, BB-1186 through BB-1263, BB-1265 through BB-1288, BB-1290 through BB-1300, BB-1302 through BB-1313, BB-1315 through BB-1384, BB-1389 through BB-1425, BB-1427 through BB-1447, BB-1449, BB-1450, BB-1452, BB-1453, BB-1455, BB-1456, BB-1458 through BB-1683, BB-1685 through BB-1716, BB-1718 through BB-1720, BB-1722, BB-1723, BB-1725, BB-1726, BB-1728 through BB-1826. (8) 200C and B200C BL-1 through BL-23, BL-25 through BL-57, BL-61 through BL-72, and BL-124 through BL-147. (9) 200CT and B200CT BN-1 through BN-4. (10) 200T and B200T BT-1 through BT-38, and BB-1314. (11) 300 and 300LW FA-1 through FA-230; and FF-1 through FF-19. (12) B300 FL-1 through FL-379. (13) B300C FM-1 through FM-10; and FN-1. (14) 1900 UA-3. (15) 1900C UB-1 through UB-74 and UC-1 through UC-174. (16) 1900D UE-1 through UE-439. (17) 65-A90-1 (U-21A or U-21G) LM-1 through LM-141. (18) 65-A90-2 (RU-21B) LS-1 through LS-3. (19) 65-A90-3 (U-21 Series) LT-1 and LT-2. (20) 65-A90-4 (U-21 Series) LU-1 through LU-16. (21) H90 (T-44A) LL-1 through LL-61. (22) A100-1 (U-21J) BB-3 through BB-5. (23) A100 (U-21F) B-95 through B-99. (24) A200 (C-12A and C-12C) BC-1 through BC-75 and BD-1 through BD-30. (25) A200C (UC-12B) BJ-1 through BJ-66. (26) A200CT (C-12D, FWC-12D, C-12F) BP-1, BP-7 through BP-11, BP-19, BP-22, and BP-24 through BP-63. (27) A200CT (RC-12D, RC-12H) GR-1 through GR-12, and GR-14 through GR-19. (28) A200CT (RC-12G) FC-1 through FC-3. (29) A200CT (RC-12K, RC-12P and RC-12Q) FE-1 through FE-9, and FE-25 through FE-36. (30) B200C (C-12F) BL-73 through BL-112, and BL-118 through BL-123; BP-64 through BP-71. (31) B200C (C-12R) BW-1 through BW-29. (32) B200C (UC-12M) BV-1 through BV-10. (33) B200C (UC-12F) BU-1 through BU-10. (34) 1900C (C-12J) UD-1 through UD-6.
Required actions
(e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspection and torque: (i) inspect the engine controls/cross shaft/pedestal for proper installation and torque; and (ii) re-torque the cross attach bolt. Initially inspect within the next 50 hours time-in-service (TIS) after October 4, 2004 (the effective date of this AD), unless already done within the last 50 hours TIS, and thereafter at intervals not to exceed 100 hours TIS until the modification in paragraph (e)(3) of this AD is done Follow Part I, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73-3634, dated September 2003. The applicable airplane maintenance manual also addresses this issue. (2) If any improper installation or wrong torque is found during any inspection required by paragraph (e)(1) of this AD, correct the installation or torque Before further flight after the inspection in which any improper installation or wrong torque is found Follow Part I, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73-3634, dated September 2003. The applicable airplane maintenance manual also addresses this issue. (3) Modify the pedestal and replace the engine controls cross shaft hardware. Modification of the pedestal and replacement of the engine controls cross shaft hardware is the terminating action for the repetitive inspection and re-torque requirements specified in paragraph (e)(1) of this AD At the next scheduled maintenance/inspection interval or 12 calendar months after October 4, 2004 (the effective date of this AD), whichever occurs later. You may do this modification before this time as terminating action for the repetitive inspection and re-torque requirements Follow Part II, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73-3634, dated September 2003. The applicable airplane maintenance manual also addresses this issue.
Unsafe condition
(d) This AD is the result of numerous reports of loose bolts on the pedestal attachment of the throttle/prop cross shaft assembly. The actions specified in this AD are intended to detect and correct loose bolts not securing the pedestal cross shaft, which could result in limited effectiveness of the control levers. This failure could lead to an aborted takeoff.
Affected ADs
(b) None.
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1