[Federal Register Volume 66, Number 133 (Wednesday, July 11, 2001)]
[Proposed Rules]
[Pages 36215-36218]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-17166]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 66, No. 133 / Wednesday, July 11, 2001 / 
Proposed Rules  

[[Page 36215]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-04-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Beech Models 
1900, 1900C (C-12J), and 1900D Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes to supersede Airworthiness Directive 
(AD) 95-02-18, which currently requires repetitive inspections of the 
engine truss assemblies for cracks on certain Raytheon Aircraft Company 
(Raytheon) Beech Models 1900, 1900C (C-12J), and 1900D airplanes, 
repair or replacement of any cracked engine truss assembly, and 
installation of reinforcement doublers. This proposed AD is the result 
of continued reports of fatigue cracks found on engine trusses on 
airplanes in compliance with AD 95-02-18. The proposed AD would require 
engine truss assembly replacement, periodic inspections and 
replacements, and the eventual incorporation of a cowling support 
installation kit as terminating action. The repetitive inspections of 
AD 95-02-18 would be retained until mandatory engine truss assembly 
replacement. The actions specified by the proposed AD are intended to 
detect and correct cracked engine truss assemblies, which could result 
in failure of the engine truss assembly and consequent loss of airplane 
control.

DATES: The Federal Aviation Administration (FAA) must receive any 
comments on this rule on or before August 30, 2001.

ADDRESSES: Submit comments in triplicate to FAA, Central Region, Office 
of the Regional Counsel, Attention: Rules Docket No. 2001-CE-04-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Comments may be 
inspected at this location between 8 a.m. and 4 p.m., Monday through 
Friday, holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. This information 
also may be examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. David L. Ostrodka, Aerospace 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4129; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

How Do I Comment on the Proposed AD?

    The FAA invites comments on this proposed rule. You may submit 
whatever written data, views, or arguments you choose. You need to 
include the rule's docket number and submit your comments in triplicate 
to the address specified under the caption ADDRESSES. The FAA will 
consider all comments received on or before the closing date. We may 
amend the proposed rule in light of comments received. Factual 
information that supports your ideas and suggestions is extremely 
helpful in evaluating the effectiveness of the proposed AD action and 
determining whether we need to take additional rulemaking action.

Are There Any Specific Portions of the Proposed AD I Should Pay 
Attention To?

    The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule that 
might suggest a need to modify the rule. You may examine all comments 
we receive before and after the closing date of the rule in the Rules 
Docket. We will file a report in the Rules Docket that summarizes each 
FAA contact with the public that concerns the substantive parts of the 
proposed AD.
    We are re-examining the writing style we currently use in 
regulatory documents, in response to the Presidential memorandum of 
June 1, 1998. That memorandum requires federal agencies to communicate 
more clearly with the public. We are interested in your comments on 
whether the style of this document is clear, and any other suggestions 
you might have to improve the clarity of FAA communications that affect 
you. You can get more information about the Presidential memorandum and 
the plain language initiative at http://www.plainlanguage.gov.

How Can I Be Sure FAA Receives My Comment?

    If you want us to acknowledge the receipt of your comments, you 
must include a self-addressed, stamped postcard. On the postcard, write 
``Comments to Docket No. 2001-CE-04-AD.'' We will date stamp and mail 
the postcard back to you.

Discussion

Has FAA Taken Any Action on the Engine Truss Assemblies of Raytheon 
Beech Models 1900, 1900C (C-12J), and 1900D Airplanes To This Point?

    Continued problems with fatigue cracking of the engine truss 
assemblies on Raytheon Beech Models 1900, 1900C (C-12J), and 1900D 
airplanes caused FAA to issue AD 95-02-18, Amendment 39-9136 (60 FR 
6652, February 3, 1995). This AD currently requires the following:

--Repetitive inspections of the engine truss assemblies for cracks;
--Repair or replacement of any cracked engine truss assembly; and
--Installation of reinforcement doublers.

What Has Happened Since AD 95-02-18 To Initiate This Action?

    The FAA continues to receive reports of engine truss fatigue cracks 
on Raytheon Beech Models 1900, 1900C (C-12J), and 1900D airplanes. The 
reports reference airplanes that are in compliance with AD 95-02-18.
    The fatigue cracks are developing as a result of operational 
stresses in joints, welded bracketry, and linoil holes sealed by drive 
screws.

Relevant Service Information

Has the Manufacturer Issued Service Information and What Are the 
Provisions of This Information?

    Raytheon has issued the following service bulletins to address this 
subject:

[[Page 36216]]



------------------------------------------------------------------------
       Service Bulletin                        Provisions
------------------------------------------------------------------------
Raytheon Aircraft Mandatory    Includes instructions for inspecting the
 Service Bulletin SB 2255,      part number (P/N) 114-910025-1, 118-
 Revision 10, Revised, June     910025-1, 118-910025-37, 118-910025-121,
 1999.                          and 129-910032-79 engine truss
                                assemblies for fatigue cracks. Also
                                includes procedures for replacing the
                                engine truss assembly with a P/N 129-
                                910047 engine truss assembly.
Raytheon Aircraft Mandatory    Includes procedures for engine truss
 Service Bulletin SB 71-3144,   assembly inspection and rework,
 Revision 1, Revised: April     including:
 1999.                         --inspection of the linoil holes and
                                replacement of the drive screws;
                               --incorporation of a cowling support
                                installation kit as terminating action
                                for the inspections.
 
Raytheon Aircraft Mandatory    Includes procedures for obtaining and
 Service Bulletin SB 71-3024,   installing a placard that specifies the
 Issued: September 1997.        part number of the engine truss
                                assembly.
------------------------------------------------------------------------

The FAA's Determination and Explanation of the Provisions of the 
Proposed AD What Has FAA Decided?

    After examining the circumstances and reviewing all available 
information related to the information described above, we have 
determined that:

--The unsafe condition referenced in this document exists or could 
develop on other Raytheon Beech Models 1900, 1900C (C-12J), and 1900D 
airplanes of the same type design;
--The inspections specified in the above-referenced service information 
should be accomplished on the affected airplanes; and
--AD action should be taken in order to detect and correct cracked 
engine truss assemblies, which could result in failure of the engine 
truss assembly and consequent loss of airplane control.

What Would the Proposed AD Require?

    This proposed AD would supersede AD 95-02-18 with a new AD that 
would require engine truss assembly replacement, periodic inspections 
and replacements, and the eventual incorporation of a cowling support 
installation kit as terminating action. The repetitive inspections of 
AD 95-02-18 would be retained until mandatory engine truss assembly 
replacement.
    Accomplishment of the proposed actions would be required in 
accordance with the previously-referenced service information.

Cost Impact

How Many Airplanes Would the Proposed AD Impact?

    We estimate that the proposed AD affects up to 236 airplanes in the 
U.S. registry.

What Would Be the Cost Impact of the Proposed AD on Owners/Operators of 
the Affected Airplanes?

    We estimate the following costs to accomplish the proposed actions:

----------------------------------------------------------------------------------------------------------------
                                                          Drive screw
                                     Engine truss       inspection and      Cowling support         Placard
                                      replacement         replacement      kit installation      installation
----------------------------------------------------------------------------------------------------------------
Number of Airplanes Affected....  12................  236...............  210...............  234
Cost Per Airplane: Workhours +    34 workhours  x     4 workhours  x      6 workhours  x      1 workhour  x  $60
 Parts Cost.                       $60 per hour +      $60 per hour +      $60 per hour +      per hour + $5 for
                                   $6,000 (average)    $12 for parts =     $35 for parts =     parts = $65 per
                                   for parts =         $252 per airplane.  $395 per airplane.  airplane.
                                   $8,040 per
                                   airplane.
Fleet Cost: Cost Per Airplane  x  $8,040  x  12       $252  x  236        $395  x  210        $65  x  234
  Number of airplanes.             airplanes =         airplanes =         airplanes =         airplanes =
                                   $96,480.            $59,472.            $82,950.            $15,210.
----------------------------------------------------------------------------------------------------------------

Regulatory Impact

Would This Proposed AD Impact Various Entities?

    The regulations proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposed rule would not have federalism 
implications under Executive Order 13132.

Would This Proposed AD Involve a Significant Rule or Regulatory Action?

    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) if promulgated, 
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 draft regulatory evaluation 
prepared for this action has been placed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 of the Federal Aviation Regulations 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. FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 
AD 95-02-18, Amendment 39-9136 (60 FR 6652, February 3, 1995), and by 
adding a new AD to read as follows:

Raytheon Aircraft Company (Beech Aircraft Corporation formerly held 
Type Certificate (TC) No. A-24CE): Docket No. 2001-CE-04-AD; 
Supersedes AD 95-02-18, Amendment 39-9136.

    (a) What airplanes are affected by this AD? This AD affects the 
following model and serial number airplanes that are certificated in 
any category:

[[Page 36217]]



------------------------------------------------------------------------
                   Model                           Serial numbers
------------------------------------------------------------------------
Beech Model 1900..........................  UA-2 and UA-3
Beech Model 1900C.........................  UB-1 through UB-74 and UC-1
                                             through UC-174
Beech Model 1900C (C-12J).................  UD-1 through UD-6
Beech Model 1900D.........................  UE-1 through UE-302
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes must comply with this AD.
    (c) What problem does this AD address? The actions specified by 
the AD are intended to detect and correct cracked engine truss 
assemblies, which could result in failure of the engine truss 
assembly and consequent loss of airplane control.
    (d) What actions must I accomplish to address this problem on 
the affected airplanes? To address this problem, accomplish the 
following:

------------------------------------------------------------------------
           Action                  Compliance            Procedures
------------------------------------------------------------------------
(1) If you do not have a      Inspect in            Inspect and replace
 part number (P/N) 129-        accordance with the   in accordance with
 910047-1, 129-910047-13, or   schedule outlined     the instructions in
 129-910047-17 engine truss    in the Appendix to    Raytheon Aircraft
 assembly (or FAA-approved     this AD (taken from   Mandatory Service
 equivalent P/N) installed,    AD 95-02-18, as       Bulletin No. 2255.
 accomplish the following:     specified in          Revision 10,
(i) Inspect the engine truss   Raytheon Aircraft     Revised, June 1999.
 assembly for cracks and       Mandatory Service     Accomplishing the
 replace any cracked truss     Bulletin No. 2255,    inspection (only)
 with a P/N truss specified    Revision 10,          using a previous
 in paragraph (d)(1)(ii) of    Revised, June,        revision to this
 this AD; and.                 1999). Replace        service bulletin is
(ii) Replace the engine        within the next 100   acceptable.
 truss assembly with a P/N     hours time-in-
 129-910047-1, 129-910047-     service (TIS) after
 13, or 129-910047-17          the effective date
 assembly (or FAA-approved     of this AD if the
 equivalent P/N)..             truss is not
                               cracked and prior
                               to further flight
                               if the truss is
                               cracked.
------------------------------------------------------------------------
(2) For airplanes equipped    Inspect upon          Accomplish
 with a P/N 129-910047-1 or    accumulating 100      inspections and
 129-910047-13 engine truss    hours TIS on the      replacements in
 assembly (or FAA-approved     engine truss          accordance with
 equivalent P/N), inspect      assembly or within    Part I of the
 for linoil hole mislocation   25 hours TIS after    ACCOMPLISHMENT
 and cracks in Area A as       the effective date    INSTRUCTIONS
 depicted in the referenced    of this AD,           section of Raytheon
 service information and       whichever occurs      Aircraft Mandatory
 replace the engine truss      later, unless         Service Bulletin SB
 assembly if any mislocated    already               71-3144, Revision
 hole or crack is found        accomplished, and     1, Revised: April,
 during any inspection.        thereafter at         1999.
                               intervals not to
                               exceed 100 hours
                               TIS. Accomplish any
                               necessary engine
                               truss assembly
                               replacement prior
                               to further flight
                               where any
                               mislocated hole or
                               crack is found.
------------------------------------------------------------------------
(3) For airplanes equipped    Inspect upon          Accomplish
 with a P/N 129-910047-1 or    accumulating 200      inspections,
 129-910047-13 engine truss    hours TIS on the      repairs, and
 assembly (or FAA-approved     engine truss          installations in
 equivalent P/N), accomplish   assembly or within    accordance with
 the following:                25 hours TIS after    Part III of the
(i) Inspect the engine         the effective date    ACCOMPLISHMENT
 cowling support bracket for   of this AD,           INSTRUCTIONS
 cracks and rework any         whichever occurs      section of Raytheon
 cracked engine cowling        later, unless         Aircraft Mandatory
 support bracket; and.         already               Service Bulletin SB
(ii) Install Kit No. 129-      accomplished, and     71-3144, Revision
 9017-1 reinforcements on      thereafter at         1, Revised: April,
 the engine cowling support    intervals not to      1999.
 bracket. The inspections      exceed 200 hours
 required by paragraph         TIS. Accomplish any
 (d)(3)(i) of this AD are no   necessary engine
 longer necessary when Kit     cowling support
 No. 129-9017-1 is             rework prior to
 incorporated..                further flight
                               where any cracked
                               bracket is found.
                               Install the engine
                               cowling support
                               bracket
                               reinforcements upon
                               accumulating 1,200
                               hours TIS on the
                               engine truss
                               assembly or within
                               the next 100 hours
                               TIS after the
                               effective date of
                               this AD, whichever
                               occurs later.
------------------------------------------------------------------------
(4) For airplanes equipped    Upon accumulating     Accomplish these
 with a P/N 129-910047-1 or    8,000 hours TIS on    replacements in
 129-910047-13 engine truss    the engine truss      accordance with
 assembly (or FAA-approved     assembly or at the    Part II of the
 equivalent P/N), replace      next engine truss     ACCOMPLISHMENT
 all remaining linoil drive    assembly removal,     INSTRUCTIONS
 screws (those not in Area     whichever occurs      section of Raytheon
 A). The inspections           later.                Aircraft Mandatory
 required by paragraph                               Service Bulletin SB
 (d)(2) of this AD are no                            71-3144, Revision
 longer required when these                          1, Revised: April,
 screws are replaced.                                1999.
------------------------------------------------------------------------
(5) For airplanes equipped    Within 12 months      Accomplish this
 with a P/N 129-910047-1 or    after the effective   installation in
 129-910047-13 engine truss    date of this AD or    accordance with the
 assembly (or FAA-approved     upon installation     ACCOMPLISHMENT
 equivalent P/N), install a    of a P/N 129-910047-  INSTRUCTIONS
 P/N 129-910047-15 truss       1 or 129-910047-13    section of Raytheon
 identification placard on     engine truss          Aircraft Service
 the engine truss assembly.    assembly, whichever   Bulletin SB.71-
                               occurs later.         3024, Issued:
                                                     September, 1997.
------------------------------------------------------------------------
(6) Do not install, on any    As of the effective   Not Applicable.
 affected airplane, an         date of this AD.
 engine truss assembly that
 is not  P/N 129-910047-1,
 129-910047-13, or 129-
 910047-17 (or FAA-approved
 equivalent P/N).
------------------------------------------------------------------------


[[Page 36218]]

    (e) Can I comply with this AD in any other way?
    (1) You may use an alternative method of compliance or adjust 
the compliance time if:
    (i) Your alternative method of compliance provides an equivalent 
level of safety; and
    (ii) The Manager, Wichita Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Wichita ACO.
    (2) Alternative methods of compliance approved in accordance 
with AD 95-02-18, which is superseded by this AD, are not approved 
as alternative methods of compliance with this AD.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Mr. David L. Ostrodka, 
Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 
Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; 
telephone: (316) 946-4129; facsimile: (316) 946-4407.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) How do I get copies of the documents referenced in this AD? 
You may obtain copies of the documents referenced in this AD from 
the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085. You may examine these documents at FAA, Central Region, Office 
of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 
64106.
    (i) Does this AD action affect any existing AD actions? This 
amendment supersedes AD 95-02-18, Amendment 39-9136.

Appendix to Docket No. 2001-CE-04-AD

    The following is the compliance schedules for the inspections 
required in this AD. These are duplicated from AD 95-02-18, 
Amendment 39-9136:
    1. 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
                Models                   figure 1 of beech SB      Initial inspection     Repetitive inspections
                                          No. 2255, Rev. VI
----------------------------------------------------------------------------------------------------------------
1900 and 1900C.......................  A......................  Upon accumulating 1,400  every 100
                                                                 hours TIS *.            hours TIS
1900 and 1900C.......................  B and C................  Upon accumulating 3,200  every 100
                                                                 hours TIS *.            hours TIS
1900D................................  A......................  Upon accumulating 3,200  every 450
                                                                 hours TIS *.            hours TIS
1900D................................  B and C................  Upon accumulating 3,200  every 3,000 hours TIS
                                                                 hours TIS *.
----------------------------------------------------------------------------------------------------------------
* or within the next 100 hours TIS after March 25, 1995 (the effective date of AD 95-02-18), whichever occurs
  later.

    2. 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                              Repetitive
of beech SB N. 2255, Rev. VI   Initial inspection        inspections
------------------------------------------------------------------------
A...........................  Upon accumulating     every 100 hours TIS
                               1,400 hours TIS *.
B...........................  Upon accumulating     every 600 hours TIS
                               1,400 hours TIS *.
C...........................  Upon accumulating     every 3,000 hours
                               1,400 hours TIS *.    TIS
------------------------------------------------------------------------
* or within the next 100 hours TIS after March 25, 1995 (the effective
  date of AD 95-02-18), whichever occurs later.


    Issued in Kansas City, Missouri, on July 3, 2001.
Dorenda D. Baker,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 01-17166 Filed 7-10-01; 8:45 am]
BILLING CODE 4910-13-P