[Federal Register Volume 66, Number 216 (Wednesday, November 7, 2001)]
[Rules and Regulations]
[Pages 56199-56202]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-27651]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-04-AD; Amendment 39-12495; AD 2001-22-16]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes Airworthiness Directive (AD) 95-02-
18, which applies to certain Raytheon Aircraft Company (Raytheon) Beech 
Models 1900, 1900C (C-12J), and 1900D airplanes. AD 95-02-18 requires 
you to repetitively inspect the engine truss assemblies for cracks, 
repair or replace any cracked engine truss assembly, and install 
reinforcement doublers. This AD requires 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 will be retained 
until mandatory engine truss assembly replacement. This AD is the 
result of continued reports of fatigue cracks found on engine trusses 
on airplanes in compliance with AD 95-02-18. The actions specified by 
this 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: This AD becomes effective on December 17, 2001.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
December 17, 2001.

ADDRESSES: You may obtain the service information referenced in this AD 
from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. You may view this 
information at the Federal Aviation Administration (FAA), Central 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2001-CE-04-AD, 901 Locust, Room 506, 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: 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.

[[Page 56200]]


SUPPLEMENTARY INFORMATION:

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.
    Has FAA taken any action to this point? The FAA issued a proposal 
to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) 
to include an AD that would apply to certain Raytheon Beech Models 
1900, 1900C (C-12J), and 1900D airplanes. This proposal was published 
in the Federal Register as a notice of proposed rulemaking (NPRM) on 
July 11, 2001 (66 FR 36215). The NPRM proposed to supersede AD 95-02-
18. The NPRM also proposed to 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.
    Was the public invited to comment? The FAA encouraged interested 
persons to participate in the making of this amendment. We did not 
receive any comments on the proposed rule or on our determination of 
the cost to the public.

FAA's Determination

    What is FAA's final determination on this issue? After careful 
review of all available information related to the subject presented 
above, we have determined that air safety and the public interest 
require the adoption of the rule as proposed except for minor editorial 
corrections. We have determined that these minor corrections:

--Provide the intent that was proposed in the NPRM for correcting the 
unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Cost Impact

    How many airplanes does this AD impact? We estimate that this AD 
affects 236 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? We estimate the following costs to accomplish the 
following 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 costs.                      $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 airpalne.  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

    Does this AD impact various entities? The regulations adopted 
herein will 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 final rule does not 
have federalism implications under Executive Order 13132.
    Does this 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) 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, under 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. 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:

2001-22-16  Raytheon Aircraft Company (Beech Aircraft Corporation 
formerly held Type Certificate (TC) No. A-24CE): Amendment 39-12495; 
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 airplane models and serial numbers that are certificated 
in any category:

[[Page 56201]]



----------------------------------------------------------------------------------------------------------------
              Model                                                  Serial No.
----------------------------------------------------------------------------------------------------------------
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 
this 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? To 
address this problem, you must accomplish the following:

----------------------------------------------------------------------------------------------------------------
                   Actions                                Compliance                        Procedures
----------------------------------------------------------------------------------------------------------------
(1) if you do not have a part number (P/N)     Inspect in accordance with the    Inspect and replace in
 129-910047-1 129-910047-13, or 129-910047-17   schedule outlined in the          accordance with the
 engine truss assembly (or FAA-approved         Appendix to this AD (taken from   instructions in Raytheon
 equivalent P/N), installed, accomplish the     AD 95-02-18, as specified in      Aircraft Mandatory Service
 following:                                     Raytheon Aircraft Mandatory       Bulletin No. 2255. Revision
(i) Inspect the engine truss assembly for       Service Bulletin No. 2255,        10, Revised, June, 1999.
 cracks and replace any cracked truss with a    Revision 10, Revised, June,       Accomplishing the inspection
 P/N truss specified in paragraph (d)(1)(ii)    1999). Replace within the next    (only) using a previous
 of this AD; and                                100 hours time-in-service (TIS)   revision to this service
(ii) Replace the engine truss assembly with a   after December 17, 2001 (the      bulletin is acceptable.
 P/N 129-910047-1, 129-910047-13, or 129-       effective date of this AD) if
 910047-17 assembly (or FAA-approved            the truss is not cracked and
 equivalent P/N)                                prior to further flight if the
                                                truss is cracked.
(2) For airplanes equipped with a P/N 129-     Inspect upon accumulating 100     Accomplish inspections and
 910047-1 or 129-910047-13 engine truss         hours TIS on the engine truss     replacements in accordance
 assembly (or FAA-approved equivalent P/N),     assembly (or within 25 hours      with Part I of the
 inspect for linoil hole mislocation and        TIS after December 17, 2001       ACCOMPLISHMENT INSTRUCTIONS
 cracks in Area A as depicted in the            (the effective date of this       section of Raytheon Aircraft
 referenced service information and replace     AD), whichever occurs later,      Mandatory Service Bulletin SB
 the engine truss assembly if any mislocated    unless already done, and          71-3144, Revision 1, Revised:
 hole or crack is found during any inspection   thereafter at intervals not to    April, 1999.
                                                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 with a P/N 129-     Inspect upon accumulating 200     Accomplish inspections,
 910047-1 or 129-910047-13 engine truss         hours TIS on the engine truss     repairs, and installations in
 assembly (or FAA-approved equivalent P/N),     assembly or within 25 hours TIS   accordance with Part III of
 accomplish the following:                      after December 17, 2001 (the      the ACCOMPLISHMENT
(i) Inspect the engine cowling support          effective date of this AD),       INSTRUCTIONS section of
 bracket for cracks and rework any cracked      whichever occurs later, unless    Raytheon Aircraft Mandatory
 engine crowling support bracket; and           already done, and thereafter at   Service Bulletin SB 71-3144,
(ii) Install Kit No. 129-9017-1                 intervals not to exceed 200       Revision 1, Revised: April,
 reinforcements on the engine cowling support   hours TIS. Accomplish any         1999.
 bracket. The inspections required by           necessary engine cowling
 paragraph (d)(3)(i) of this AD are no longer   support rework prior to further
 necessary when Kit No. 129-9017-1 is           flight where any cracked
 incorporated                                   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 December 17, 2001 (the
                                                effective date of this AD),
                                                whichever occurs later.
(4) For airplanes equipped with a P/N 129-     Upon accumulating 8,000 hours     Accomplish these replacements
 910047-1 or 129-910047-13 engine truss         TIS on the engine truss           in accordance with Part II of
 assembly (or FAA-approved equivalent P/N),     assembly or at the next engine    the ACCOMPLISHMENT
 replace all remaining linoil drive screws      truss assembly removal,           INSTRUCTIONS section of
 (those not in Area A). The inspections         whichever occurs later.           Raytheon Aircraft Mandatory
 required by paragraph (d)(2) of this AD are                                      Service Bulletin SB 71-3144,
 no longer required when these screws are                                         Revision 1, Revised: April,
 replaced                                                                         1999.
(5) For airplanes equipped with a P/N 129-     Within 12 months after December   Accomplish this installation in
 910047-1 or 129-910047-13 engine truss         17, 2001 (the effective date of   accordance with the
 assembly (or FAA-approved equivalent P/N),     this AD) or upon installation     ACCOMPLISHMENT INSTRUCTIONS
 install a P/N 129-910047-15 truss              of a P/N 129-910047-1 or 129-     section of Raytheon Aircraft
 identification placard on the engine truss     910047-13 engine truss            Service Bulletin SB.71-3024,
 assembly                                       assembly, whichever occurs        Issued: September, 1997.
                                                later.
(6) Do not install, on any affected airplane,  As of December 17, 2001 (the      Not Applicable.
 an engine truss assembly that is not P/N 129-  effective date of this AD).
 910047-1, 129-910047-13, or 129-910047-17
 (or FAA-approved equivalent P/N)
----------------------------------------------------------------------------------------------------------------


[[Page 56202]]

    (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 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) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Raytheon Aircraft Mandatory Service Bulletin No. 2255. Revision 
10, Revised, June, 1999, Raytheon Aircraft Mandatory Service 
Bulletin SB 71-3144, Revision 1, Revised: April, 1999, and Raytheon 
Aircraft Service Bulletin SB.71-3024, Issued: September, 1997. The 
Director of the Federal Register approved this incorporation by 
reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may obtain 
copies from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 
67201-0085. You may view this information at FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, 
Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (i) Does this AD action affect any existing AD actions? This 
amendment supersedes AD 95-02-18, Amendment 39-9136.
    (j) When does this amendment become effective? This amendment 
becomes effective on December 17, 2001.

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              Repetitive inspections
                                    No. 2255, Rev. VI        inspection
----------------------------------------------------------------------------------------------------------------
1900 and 1900C.................  A.....................  Upon accumulating  Every 100 hours TIS.
                                                          1,400 hours TIS*.
1900 and 1900C.................  B and C...............  Upon accumulating  Every 100 hours TIS.
                                                          3,200 hours TIS*.
1900D..........................  A.....................  Upon accumulating  Every 450 hours TIS.
                                                          3,200 hours TIS*.
1900D..........................  B and C...............  Upon accumulating  Every 3,000 hours TIS.
                                                          3,200 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 of Beech SB
           N. 2255,  Rev. VI                 Initial inspection                Repetitive inspections
----------------------------------------------------------------------------------------------------------------
A......................................  Upon accumulating 1,400    Every 100 hours TIS.
                                          hours TIS*.
B......................................  Upon accumulating 1,400    Every 600 hours TIS.
                                          hours TIS*.
C......................................  Upon accumulating 1,400    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.


    Issued in Kansas City, Missouri, on October 26, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 01-27651 Filed 11-6-01; 8:45 am]
BILLING CODE 4910-13-P