| AD Number | 93-25-07 | Status | Superseded |
| Effective Date | February 15, 1994 | Issue Date | Not specified |
| Docket Number | 93-CE-38-AD | Amendment | 39-8773 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small/Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Raytheon Aircraft Company |
| Model(s) | 200 Model or Series (all) 200C 200CT 200T 300 A100-1 (U-21J) A200 A200 (C-12A) A200 (C-12C) A200C (UC-12B) A200CT (C-12D) A200CT (C-12F) A200CT (FWC-12D) A200CT (RC-12D) A200CT (RC-12G) A200CT (RC-12H) A200CT (RC-12K) A200CT (RC-12P) A200CT (RC-12Q) B200 B200C B200CT B200T B300 B300C |
| Superseded By | 2005-01-18 |
93-25-07 BEECH AIRCRAFT CORPORATION: Amendment 39-8773. Docket No. 93-CE-38-AD.
Applicability: The model and serial number airplanes presented below, certificated in any category, that do not have all the fuselage stringers Nos. 5 through 11 modified on both the right and left hand sides in accordance with either (1) Beech Service Bulletin (SB) 2472, Revision 1, dated September 1993; (2) Chapter 51-10 or 53-10, as applicable, of the maintenance manual; or (3) the instructions to Priester Aviation Service Supplemental Type Certificate (STC) SA63CH:
Models
Serial Numbers
200, A200, B200,
and A100-1
BB-2 through BB-1462, BC-1 through
BC-75, and BD-1 through BD-30
200C, A200C, and
B200C
BL-1 through BL-138, BJ-1 through
BJ-66, BU-1 through BU-12, and BV-1through BV-12
200CT, A200CT,
B200CT
BN-1 through BN-4, BP-1 through
BP-71, FC-1, FC-2, FC-3, FE-1
through FE-31, FG-1, FG-2, and GR-1 through GR-19
200T and B200T
BT-1 through BT-38
300
FA-1 through FA-228
300 (FAA)
FF-1 through FF-19
B300
FL-1 through FL-103
B300C
FM-1 through FM-8 and FN-1
Compliance: Required upon the accumulation of 3,000 hours time-in-service (TIS) or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, unless already accomplished, and thereafter as indicated.
To prevent structural damage to the fuselage caused by cracked stringers in the rear pressure bulkhead area, accomplish the following:
(a) Inspect fuselage stringers Numbers (Nos.) 5 through 11 on both the left and right hand sides for cracks in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB No. 2472, Revision 1, dated September 1993.
(1) If no cracks are found, reinspect at intervals that correspond with the following:
Stringers Modified in Accordance With
One of the Three Modifications Referenced
in the Applicability Section of this AD
Inspection Interval
No Stringers Modified
600 hours TIS on all stringers
Nos. 8, 9, and 10 (one side) with
Internal Modification
1,200 hours TIS on unmodified
stringers
Nos. 8, 9, and 10 (one side) with
External Modification
600 hours TIS on unmodified
stringers
Nos. 5 through 11
AD no longer applies
(2) If cracks are found, modify all cracked fuselage stringers at any time up to the time specified in the chart presented in paragraph (a)(3) of this AD. Accomplish this modification in accordance with the instructions in one of the three modifications specified in the Applicability section of this AD, and reinspect at intervals presented in the chart in paragraph (a)(1) of this AD.
(3) The following chart specifies the required compliance time where cracked stringers must be modified:
No. of Stringers Cracked on Any
One Side of Fuselage
When Modification Must
be Accomplished (Hours TIS)
1 to 3
150
4
30
5 or more
Prior to further flight
(b) The modifications specified in the Applicability section of this AD may be accomplished at any time as terminating action for the inspection requirement of this AD provided that all fuselage stringers Nos. 5 through 11 are modified.
(c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita ACO.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO.
(e) The inspections and modification required by this AD shall be done in accordance with Beech Service Bulletin 2472, Revision 1, dated September 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(f) This amendment (39-8773) becomes effective on February 15, 1994.