[Federal Register Volume 62, Number 94 (Thursday, May 15, 1997)]
[Rules and Regulations]
[Pages 26737-26739]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-12516]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-27-AD; Amendment 39-10026; AD 97-10-14]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Model 1900D 
Airplanes (formerly Beech Aircraft Corporation)

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Raytheon Aircraft Company

[[Page 26738]]

(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.

DATES: Effective July 7, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 7, 1997.

ADDRESSES: Service information that applies to this AD may be obtained 
from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may also be examined at the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket 96-CE-27-AD, Room 1558, 601 E. 12th 
Street, Kansas City, Missouri 64106; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Steven E. Potter, Aerospace 
Engineer, Wichita Aircraft Certification Service, 1801 Airport Rd., Rm. 
100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-
4124; facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION:

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 approximately 1 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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

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

[[Page 26739]]

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 Aircraft 
Certification 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 (39-10026) becomes effective on July 7, 1997.

    Issued in Kansas City, Missouri, on May 7, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-12516 Filed 5-14-97; 8:45 am]
BILLING CODE 4910-13-U