AD 97-10-14

This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) Model 1900D airplanes (formerly referred to as Beech Aircraft Corporation Model 1900D). This action requires inspecting the stabilon attachment angles for the correct thickness, repetitively inspecting for cracks, and replacing the attachment angles that are the incorrect thickness with ones of the correct thickness. Recent reports of the affected airplanes having the incorrect size stabilon attachment angles prompted this action. The actions specified by this AD are intended to prevent separation of the stabilon from the airplane, which could cause loss of airplane stability during flight.

Final rule

97-10-14 RAYTHEON AIRCRAFT COMPANY (formerly Beech Aircraft Corporation): Amendment 39-10026; Docket No. 96-CE-27-AD.

Applicability: Model 1900D airplanes (serial numbers UE-1 through UE-215), 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 request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD, and thereafter as indicated in the body of this AD, unless already accomplished.

To prevent separation of the stabilons from the airplane, which could cause loss of airplane stability during flight, accomplish the following:

(a) Inspect the left and right stabilon attachment angles for proper thickness, which is .090-inch thick in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beechcraft Mandatory Service Bulletin (MSB) No. 2651, Issued: January 1996.

(b) If the attachment angles are not the correct thickness and measure only .071-inch thick, accomplish the following in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beechcraft MSB No. 2651, Issued: January 1996:

(1) Repetitively inspect the stabilon attachment angles for cracks, at intervals not to exceed 50 hours TIS, until cracks are visible;

(2) When cracks are visible, prior to further flight, replace the attachment angles with attachment angles of the correct thickness (.090-inch thick); and

(3) If no cracks are visible during any of the inspections required by this AD, within the next 600 hours TIS after the effective date of this AD, replace the 0.071-inch thick attachment angles with 0.090-inch thick attachment angles.

(c) Replacing the 0.071-inch thick stabilon attachment angles with 0.090-inch thick attachment angles at any time after the effective date of this AD terminates the repetitive inspection requirements of this AD.

(d) 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.

(e) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita AircraftCertification Service, 1801 Airport Rd., Rm. 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office.

(f) The inspections and replacements required by this AD shall be done in accordance with Beechcraft Mandatory Service Bulletin No. 2651, Issued: January 1996. 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, 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.

(g) This amendment becomes effective on July 7, 1997.

Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to Raytheon Model 1900D airplanes was published in the Federal Register on October 23, 1996 (61 FR 54965). The action proposed to require:

- Inspecting the left and right stabilon attachment angles for proper thickness, which is .090-inch thick;

- If the attachment angles are not the correct thickness (.090-inch thick), the proposed AD would require:

- Repetitively inspecting the stabilon attachment angles for cracks until cracks are visible,

- Replacing the attachment angles with attachment angles of the correct thickness (.090-inch thick) when cracks become visible, and

- If no cracks are visible during the inspections, replacing the attachment angles with attachment angles of the correct thickness.

- The replacement of the stabilon attachment angles with angles of the correct thickness will terminate the inspection requirements of this AD.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposed rule or the FAA's determination of the cost to the public.

Accomplishment of this action would be in accordance with Beechcraft Mandatory Service Bulletin No. 2651, Issued: January 1996.

The FAA's Determination
After careful review of all available information related to the subject presented above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial corrections. The FAA has determined that these minor corrections will not change the meaning of the AD and will not add any additional burden upon the public than was already proposed.

Cost Impact
The FAA estimates that 215 airplanes in the U.S. registry will be affected by this AD, that it will take approximately1 hour per airplane to accomplish the initial inspection, and that the average labor rate is approximately $60 an hour. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $12,900 or $60 per airplane. This figure is only accounting for the initial inspection and possible replacement of the stabilon attachment angles and is not considering the number of repetitive inspections that may be incurred over the life of the airplane.

Regulatory Impact
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 copy of the final evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting 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), 40113, 44701.

39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows: