- Effective
- March 24, 2004
- Published
- February 18, 2004 · 69 FR 7555–7556
- Issued
- February 5, 2004
- Models
- 400A, 400T
- Data sheet
- TCDSA16SW
- Registered aircraft
- 299 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-13479
- Docket
- 2002-NM-225-AD
- Issued as
- Final rule
Unofficial copy from the Federal Register XML, document 04-3203. Only the govinfo PDF is the legal edition. DRS record last changed January 21, 2026.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 134 KB | 53caebf0…39be464 | 04-3203.pdf on govinfo.gov |
| Federal Register XML | 12 KB | e01f3bf9…694d6d2 | 04-3203.xml on federalregister.gov |
| FAA DRS HTML attachment | 42 KB | d62503f3…5337d39 | FAA DRS (API key needed) |
| FAA DRS PDF | 28 KB | b5465528…4ccf75d | FAA DRS (API key needed) |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Beech 400A and 400T series airplanes, that requires an inspection to determine the part number of the A194 roll trim printed circuit board (PCB), and replacement of certain PCBs with improved parts. This action is necessary to prevent intermittent sticking of the relays on the PCB in either the open or closed position, which could result in an out-of-trim condition that could require using considerable control wheel force to keep the wings level, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
The airworthiness directive
2004-03-35 Raytheon Aircraft Company (Formerly Beech): Amendment 39-13479. Docket 2002-NM-225-AD.
Applicability: Model Beech 400A series airplanes having serial numbers RK-45, and RK-49 through RK-322 inclusive; and Model 400T series airplanes having serial numbers TT-1 through TT-180 inclusive, and TX-1 through TX-12 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent intermittent sticking of the relays on the roll trim printed circuit board (PCB) in either the open or closed position, which could result in an out-of-trim condition that could require using considerable control wheel force to keep the wings level, and consequent reduced controllability of the airplane, accomplish the following:
(a) Inspection and Replacement, if Necessary
PDF page 1(a) Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, perform an inspection to determine the part number of the A194 roll trim PCB, in accordance with Raytheon Service Bulletin SB 27-3464, dated December 2001.
(1) If the A194 roll trim PCB has a part number of 128-364122-7 or higher ( i.e., 128-364122-9, -11, etc.): No further action is required by this paragraph.
(2) If the A194 roll trim PCB does not have a part number of 128-364122-7 or higher: Before further flight, replace the A194 roll trim PCB with a PCB having a part number of 128-364122-7 or higher, in accordance with the service bulletin.
(b) Parts Installation
PDF page 2(b) As of the effective date of this AD, no person may install on any airplane an A194 roll trim PCB having part number 128-364122-1 or 128-364122-5.
(c) Alternative Methods of Compliance
PDF page 2(c) In accordance with 14 CFR 39.19, the Manager, Wichita Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance for this AD.
(d) Incorporation by Reference
PDF page 2(d) The actions must be done in accordance with Raytheon Service Bulletin SB 27-3464, dated December 2001. 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 Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.
(e) Effective Date
PDF page 2(e) This amendment becomes effective on March 24, 2004.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
DatesPage 1
Effective March 24, 2004.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 24, 2004.
AddressesPage 1
The service information referenced in this AD may be obtained from Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, Kansas 67201-0085. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.
For further information contactPage 1
Philip Petty, Aerospace Engineer, Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4139; fax (316) 946-4407.
Supplementary informationPage 1
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Raytheon Model Beech 400A and 400T series airplanes was published in the Federal Register on November 4, 2003 (68 FR 62415). That action proposed to require an inspection to determine the part number of the A194 roll trim printed circuit board (PCB), and replacement of certain PCBs with improved parts.
CommentsPage 1
We provided the public the opportunity to participate in the development of this AD. No comments have been submitted on the proposed AD or on the determination of the cost to the public.
ConclusionPage 1
We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.
Cost impactPage 1
There are approximately 467 airplanes of the affected design in the worldwide fleet. The FAA estimates that 430 airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the required actions, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $27,950, or $65 per airplane.
The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.
Regulatory impactPage 1
The regulations adopted herein will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.
Adoption of the amendmentPage 1
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
1. The authority citation for part 39 continues to read as follows:
2. Section 39.13 is amended by adding the following new airworthiness directive:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 299
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1988 | 1 |
|---|---|
| 1990 | 3 |
| 1991 | 6 |
| 1992 | 8 |
| 1993 | 2 |
| 1994 | 7 |
| 1995 | 4 |
| 1996 | 8 |
| 1997 | 17 |
| 1998 | 20 |
| 1999 | 28 |
| 2000 | 21 |
| 2001 | 17 |
| 2002 | 9 |
| 2003 | 2 |
| 2004 | 8 |
| 2005 | 10 |
| 2006 | 12 |
| 2007 | 20 |
| 2008 | 19 |
| 2009 | 1 |
| 2010 | 2 |
| 2016 | 1 |
73 with no year recorded