- Effective
- January 16, 1996
- Published
- December 15, 1995 · 60 FR 64315–64316
- Model
- 400A
- Data sheet
- TCDSA16SW
- Registered aircraft
- 298 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-9450
- Docket
- 95-NM-75-AD
- Issued as
- Final rule
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. 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 | 117 KB | b727d5d6…d42000b | 95-30533.pdf on govinfo.gov |
| FAA DRS HTML | 43 KB | b2453dbd…3a4bc64 | FAA DRS (API key needed) |
| Federal Register text | 10 KB | a9cf2ba4…81cd80c | 95-30533.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400A airplanes, that requires an inspection to verify if the securing rivet is installed on the rod end of the control push rods of the spoiler flight control system, an inspection to verify if the jam nut is secure on the opposite end of the rod end, and repair of any discrepancy. This amendment is prompted by a report of loss of roll control on the co-pilot's control wheel shortly after takeoff due to a rivet missing from the control push rod. The actions specified by this AD are intended to ensure that the push rod rivets are installed. Missing control push rod rivets could result in the disengagement of the push rod end from the push rod tube; this could lead to loss of roll control and subsequent reduced controllability of the airplane after takeoff.
The airworthiness directive
95-25-05 BEECH AIRCRAFT CORPORATION: Amendment 39-9450. Docket 95-NM-75-AD.
Applicability: Model 400A airplanes, serial numbers RK-1 through RK-96 inclusive, certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case doesthe presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced controllability of the airplane after takeoff, accomplish the following:
(a) Within 50 hours time-in-service after the effective date of this AD, perform a detailed visual inspection to verify if the securing rivet is installed on the control push rods of the spoiler flight control system, and an inspection to verify if the jam nut is secure on the opposite rod end, in accordance with Beechcraft Safety Communique 400A-113, dated March 1995. If any discrepancy is found, prior to further flight, repair in accordance with a method approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate.
(b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita ACO, FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO.
(c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
(d) The inspections shall be done in accordance with Beechcraft Safety Communique 400A-113, dated March 1995. 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 Beech Aircraft Corporation, Commercial Service Department, 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, Small Airplane Directorate, 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) This amendment becomes effective on January 16, 1996.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
Supplementary information
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 Beech Model 400A airplanes was published in the Federal Register on August 10, 1995 (60 FR 40782). That action proposed to require a one-time detailed visual inspection to verify if the securing rivet is installed on the push rods of the spoiler flight control system. That action also proposed to require an inspection to verify if the jam nut is secure on the opposite rod end, and repair of any discrepancy.
No comments were submitted in response to the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
There are approximately 96 Model 400A airplanes of the affected design in the worldwide fleet. The FAA estimates that 73 airplanes of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $35,040, or $480 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 regulations adopted herein will not have substantial direct effects 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, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.
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."
List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment 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:
PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 USC 106(g), 40101, 40113, 44701.
39.13 - [Amended] 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 · 298
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 |
72 with no year recorded