[Federal Register Volume 60, Number 23 (Friday, February 3, 1995)]
[Rules and Regulations]
[Pages 6652-6654]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-2403]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-CE-41-AD; Amendment 39-9136; AD 95-02-18]
Airworthiness Directives; Beech Aircraft Corporation Models 1900,
1900C, and 1900D Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 92-06-
09, which currently requires repetitively inspecting the engine trusses
for cracks on Beech Aircraft Corporation (Beech) Model 1900 and certain
Model 1900C airplanes, repairing or replacing any cracked engine truss,
and installing reinforcement doublers. That AD also provides the option
of installing an engine truss of improved design as terminating action
for the repetitive inspections. Since issuing that AD, the Federal
Aviation Administration (FAA) has received several reports of these
improved design trusses cracking in Area A (as specified in the service
information) of the engine truss. This action retains the currently
required repetitive inspections, but shortens the repetitive inspection
interval in Area A and eliminates the inspection-terminating
replacement option; and also incorporates the Beech Models 1900C and
1900D airplanes that have engine trusses of this same type design
installed at manufacture. The actions specified by this AD are intended
to prevent failure of the engine truss assembly caused by a cracked
engine truss.
DATES: Effective March 25, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 25, 1995.
ADDRESSES: Service information that applies to this AD may be obtained
from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas
67201-0085. This information may also be examined at the FAA, Central
Region, Office of the Assistant Chief Counsel, 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, Wichita Aircraft
Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport,
Wichita, Kansas 67209; telephone (316) 946-4124; facsimile (316) 946-
4407.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that would apply
to Beech Model 1900 and certain Model 1900C airplanes was published in
the Federal Register on December 1, 1993 (58 FR 63305). The action
proposed to supersede AD 92-06-09 with a new AD that would (1) retain
the repetitive inspection requirements of AD 92-06-09, extend the
applicability to include Beech Models 1900C and 1900D airplanes that
have a part number 129-910032-79 engine truss installed, and shorten
the repetitive inspection interval of Area A (as specified in the
service information) of the engine truss to 100 hours TIS; and (2)
eliminate the option of terminating the repetitive inspections on the
Beech Model 1900 and 1900C airplanes if an improved design engine
truss, 129-910032-79, is installed. The inspections were proposed to be
accomplished in accordance with Beech Service Bulletin (SB) No. 2255,
Revision V, dated October 1993.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
One commenter concurs with the proposal as written.
The other commenter concurs with the actions specified in the
proposal, but states that the engine trusses on the Beech Model 1900
airplanes are hard to identify. This commenter states that Beechcraft
1900 Airliner Communique No. 27, dated February 1993, presents
information that helps identify the older engine trusses, and
recommends that the FAA reference this document in the proposal. The
FAA concurs that the Beech Model 1900 airplane engine trusses are hard
to identify, and that Beechcraft 1900 Airliner Communique No. 27, dated
February 1993, helps identify these trusses. A NOTE has been added in
the proposal that references this service communique as a document that
could be used in identifying engine trusses.
In addition, Beech has revised SB 2255 to the Revision VI level
(dated August 1994). This document revises the inspection schedule for
airplanes having engine truss part number 129-910032-79. Implementation
of this schedule would be a reduction from that already proposed. The
FAA has determined that this SB should be incorporated into the
proposal.
After careful review of all available information including the
comments referenced above, the FAA has determined that air safety and
the public interest require the adoption of the rule as proposed except
for the addition of the NOTE, the incorporation of Beech SB No. 2255,
Revision VI, dated August 1994, and minor editorial corrections. The
FAA has determined that this minor addition, the SB incorporation, and
the editorial corrections will not change the meaning of the AD or add
any additional burden upon the public than was already proposed.
The FAA estimates that 279 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 16 workhours per
airplane to accomplish the required inspection (one-time in all
applicable areas), and that the average labor rate is approximately $60
an hour. Based on these figures, the total cost impact of the AD on
U.S. operators is estimated to be $267,840. The only additional cost
impact on U.S. operators by the required action over that which is
currently required by AD 92-06-09 is the [[Page 6653]] required
inspections on 77 Beech Models 1900C and 1900D airplanes or $73,920 (16
workhours x $60 x 77 airplanes). These figures are based on the
assumption that no affected airplane owner/operator has accomplished
the required initial inspection, and do not account for the cost of
repetitive inspections. The FAA has no way of determining the number of
repetitive inspections each owner/operator would incur.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing AD 92-06-09, Amendment 39-
8189 (57 FR 8060, March 6, 1992), and by adding a new AD to read as
follows:
95-02-18 Beech Aircraft Corporation: Amendment 39-9136; Docket No.
93-CE-41-AD. Supersedes AD 92-06-09, Amendment 39-8189.
Applicability: Models 1900, 1900C, and 1900D airplanes (all
serial numbers), certificated in any category.
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To prevent failure of the engine truss assembly caused by a
cracked engine truss, accomplish the following:
(a) For Models 1900 and 1900C airplanes with either engine truss
part number (P/N) 114-910025-1 or P/N 118-910025-1 installed that is
not equipped with reinforcement doublers at the engine firewall
attachment bosses, upon the accumulation of 1,400 hours TIS or
within the next 100 hours TIS after the effective date of this AD,
whichever occurs later, install reinforcement doublers in accordance
with the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service
Bulletin (SB) No. 2255, Revision VI, dated August 1994.
(b) For all affected airplanes having engine truss P/N 129-
910032-79 installed, initially and repetitively inspect the engine
truss for cracks at the weld joints in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Beech SB 2255, Revision VI,
dated August 1994, at the times specified in the following chart:
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Area specified in figure
Models 1 of Beech SB No. 2255, Initial inspection Repetitive inspection
Rev. VI
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1900 and 1900C........... A....................... Upon accumulating 1,400 hours Every 100 hours TIS.
TIS*.
1900 and 1900C........... B and C................. Upon accumulating 3,200 hours Every 100 hours TIS.
TIS*.
1900D.................... A....................... Upon accumulating 3,200 hours Every 450 hours TIS.
TIS*.
1900D.................... B and C................. Upon accumulating 3,200 hours Every 3,000 hours TIS.
TIS*.
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*Or within the next 100 hours TIS after the effective date of this AD, whichever occurs later.
(c) For all Models 1900 and 1900C airplanes having engine truss P/N
118-9100-25-37, P/N 118-910025-121, P/N 114-910025-1 or P/N 118-910025-
1, initially and repetitively inspect the engine truss for cracks at
the weld joints in accordance with the ACCOMPLISHMENT INSTRUCTIONS
section of Beech Service Bulletin (SB) 2255, Revision VI, dated August
1994, at the times specified in the following chart:
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Area
specified in
figure 1 of Initial inspection Repetitive
Beech SB N. inspection
2255, Rev. VI
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A............ Upon accumulating 1,400 hours TIS*..... Every 100 hours
TIS.
B............ Upon accumulating 1,400 hours TIS*..... Every 600 hours
TIS.
C............ Upon accumulating 1,400 hours TIS*..... Every 3,000
hours TIS.
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*Or within the next 100 hours TIS after the effective date of this AD,
whichever occurs later.
Note 1: Beechcraft 1900 Airliner Communique No. 27, dated
February 1993, provides information for identifying engine trusses
on Beech Model 1900 airplanes. Copies of this document may be
obtained from the Wichita Aircraft Certification Office (ACO) at the
address specified in paragraph (f) of this AD.
(d) If any cracks are found during the inspections required by
paragraphs (b) and (c) of this AD, prior to further flight, repair the
crack or replace the engine truss with one of the applicable truss part
numbers specified in the following table, and reinspect the truss at
the times previously specified:
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Truss part No. Models Instructions
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118-910025-37 1900 and 1900C......... Applicable Maintenance
(serviceable truss). Manual.
118-910025-121 1900 and 1900C......... Applicable Maintenance
(serviceable truss). Manual.
129-910032-79.......... 1900, 1900C and 1900D.. Beech Kit 114-9036-1
or 114-9036-3.
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[[Page 6654]]
Note 2: Installation of an improved design engine truss, P/N
129-910032-79, on any of the affected airplanes does not eliminate
the repetitive inspection requirement of this AD.
Note 3: Compliance with a previous revision level of the service
bulletin referenced in this AD fulfills the applicable requirements
of this AD and is considered ``unless already accomplished''.
(e) Special flight permits may be issued in accordance with
Secs. 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.
(f) 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 ACO, FAA,
1801 Airport Road, 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 ACO.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(g) The inspections and replacement (if necessary) required by
this AD shall be done in accordance with Beech Service Bulletin No.
2255, Revision VI, dated August 1994. 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 the Beech Aircraft Corporation, 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.
(h) This amendment (39-9136) supersedes AD 92-06-09, Amendment
39-8189.
(i) This amendment (39-9136) becomes effective on March 25,
1995.
Issued in Kansas City, Missouri, on January 26, 1995.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-2403 Filed 2-2-95; 8:45 am]
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