[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:

----------------------------------------------------------------------------------------------------------------
                           Area specified in figure                                                             
          Models            1 of Beech SB No. 2255,        Initial inspection           Repetitive inspection   
                                    Rev. VI                                                                     
----------------------------------------------------------------------------------------------------------------
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:

------------------------------------------------------------------------
     Area                                                               
 specified in                                                           
 figure 1 of              Initial inspection               Repetitive   
 Beech SB N.                                               inspection   
2255, Rev. VI                                                           
------------------------------------------------------------------------
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.     
------------------------------------------------------------------------
*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:

------------------------------------------------------------------------
     Truss part No.               Models               Instructions     
------------------------------------------------------------------------
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.       
------------------------------------------------------------------------


[[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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