[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
