[Federal Register Volume 70, Number 12 (Wednesday, January 19, 2005)]
[Rules and Regulations]
[Pages 2941-2944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-716]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-CE-01-AD; Amendment 39-13943; AD 2005-01-18]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Beech 100, 
200, and 300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA adopts a new airworthiness directive (AD) to supersede 
AD 93-25-07, which applies to Raytheon Aircraft Company (Raytheon) 
Beech 100, 200, and 300 series airplanes. AD 93-25-07 currently 
requires you to repetitively inspect the fuselage stringers for cracks 
and modify at certain times depending on the number of cracked 
stringers. This AD is the result of FAA's policy (since 1996) to not 
allow airplane operation when known cracks exist in primary structure. 
The fuselage structure is considered primary structure and operation is 
currently allowed for a certain period of time if less than five 
fuselage stringers are cracked. Consequently, this AD retains the 
inspection and modification requirements of AD 93-25-07, but requires 
you to repair any cracked fuselage stringers. We are issuing this AD to 
detect and correct any cracked fuselage stringers in the rear pressure 
bulkhead area, which could result in structural damage to the fuselage. 
This damage could lead to failure of the fuselage with potential loss 
of control of the airplane.

DATES: This AD becomes effective on March 1, 2005.
    As of March 1, 2005, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in the 
regulation.

ADDRESSES: You may get the service information identified in this AD 
from Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140.
    You may view the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2004-CE-01-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. 
to 4 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Steven E. Potter, Aerospace Engineer, 
Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road, 
Wichita, Kansas 67209; telephone: (316) 946-4124; facsimile: (316) 946-
4107.

SUPPLEMENTARY INFORMATION:

Discussion

    What events have caused this AD? Reports of cracks on the fuselage 
stringers in the rear pressure bulkhead area on Raytheon Beech 100, 
200, and 300 series airplanes caused us to issue AD 93-25-07, Amendment 
39-8773. AD 93-25-07 currently requires the following on Raytheon Beech 
Models 200, A200, B200, A100-1, 200C, A200C, B200C, 200CT, A200CT, 
B200CT, 200T, B200T, 300, B300, and B300C airplanes:

--Repetitive inspections of the fuselage stringers for cracks; and
--Modification at certain times depending on the number of cracked 
stringers.

    What has happened since AD 93-25-07 to initiate this action? As 
currently written, AD 93-25-07 allows continued flight if cracks are 
found in less than five fuselage stringers in the area of the rear 
pressure bulkhead. In 1996, FAA developed policy to not allow airplane 
operation when known cracks exist in primary structure, unless the 
ability to sustain limit and ultimate load with these cracks is proven. 
The fuselage stringers in the area of the rear pressure bulkhead are 
considered primary structure.
    This AD brings the actions of AD 93-25-07 in compliance with FAA 
policy. Therefore, FAA has determined:

--That airplane operation on the affected airplanes should not be 
allowed for more than 25 hours time-in-service (TIS) if less than five 
fuselage stringers (Stringer Nos. 5 through 11) in the rear pressure 
bulkhead are cracked; and
--That no operation should be allowed until modification for any 
airplane with five or more cracked fuselage stringers (Stringer Nos. 5 
through 11) in the rear pressure bulkhead.

    The FAA has also identified other airplanes that should be affected 
by this action.
    What is the potential impact if FAA took no action? Cracked 
fuselage stringers in the rear pressure bulkhead area, if not detected 
and corrected, could result in structural damage to the fuselage. This 
damage could lead to failure of the fuselage with potential loss of 
control of the airplane.
    Has FAA taken any action to this point? We 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 100, 200, and 
300 series airplanes. This proposal was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on September 14, 
2004 (69 FR 55369). The NPRM proposed to supersede AD 93-25-07 with a 
new AD that would retain the requirement of repetitively inspecting the 
fuselage stringers for cracks, but would require the repair of any 
cracked fuselage stringers. We also proposed a grace period of 25 
cycles for all airplanes with less than five cracked fuselage 
stringers. The repetitive inspections would no longer be required when 
all fuselage stringers (Nos. 5 though 11) in the rear pressure bulkhead 
are modified.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. We received no 
comments on the proposal or on the determination of the cost to the 
public.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for minor 
editorial corrections. We have determined that these minor corrections:

--Are consistent with 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.

[[Page 2942]]

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the FAA's AD system. This regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    How many airplanes does this AD impact? We estimate that this AD 
affects 2,300 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 each 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                           Total
                Labor cost                          Parts cost            cost per       Total cost on  U.S.
                                                                          airplane            operators
----------------------------------------------------------------------------------------------------------------
2 workhours x $65 per hour = $130........  No special parts necessary         $130       $130 x 2,300 = $299,000
                                            to do the inspection..
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to incorporate the fuselage 
stringer repair kit that will be required based on the results of each 
inspection. We have no way to determine the number of airplanes that 
may need this repair kit:

------------------------------------------------------------------------
                                                        Total cost per
           Labor cost                 Parts cost           airplane
------------------------------------------------------------------------
11 workhours x $65 per hour $715  Approximately $200  Ranging from $915
                                   per repair kit      per airplane to
                                   with one to three   $1,315 per
                                   kits necessary      airplane.
                                   depending on the
                                   extent of the
                                   cracks (possible
                                   total of $600 per
                                   airplane).
------------------------------------------------------------------------

Regulatory Findings

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD 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.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2004-CE-01-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
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]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
93-25-07, Amendment 39-8773, and by adding a new AD to read as follows:

2005-01-18 Raytheon Aircraft Company: Amendment 39-13943; Docket No. 
2004-CE-01-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on March 1, 2005.

What Other ADs Are Affected by This Action?

    (b) This AD supersedes AD 93-25-07, Amendment 39-8773.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following Beech airplane models and 
serial numbers that are certificated in any category:

------------------------------------------------------------------------
                   Model                             Serial Nos.
------------------------------------------------------------------------
(1) A100-1 (U-21J)........................  BB-3 through BB-5
(2) 200 and B200..........................  BB-2 and BB-6 through BB-
                                             1462.
(3) A200 (C-12A) and A200 (C-12C).........  BC-1 through BC-75 and BD-1
                                             through BD-30.
(4) A200C (UC-12B)........................  BJ-1 through BJ-66.
(5) A200CT (C-12D)........................  BP-1, BP-22, and BP-24
                                             through BP-51.
(6) A200CT (FWC-12D)......................  BP-7 through BP-11.
(7) A200CT (RC-12D).......................  GR-1 through GR-13.
(8) A200CT (C-12F)........................  BP-52 through BP-63.
(9) A200CT (RC-12G).......................  FC-1 and FC-3.
(10) A200CT (RC-12H)......................  GR-14 through GR-19.
(11) A200CT (RC-12K)......................  FE-1 through FE-9.
(12) A200CT (RC-12P)......................  FE-10 through FE-24.
(13) A200CT (RC-12K)......................  FE-25 through FE-31.
(14) 200C and B200C.......................  BL-1 through BL-72 and BL-
                                             124 through BL-138.
(15) 200CT................................  BN-1 through BN-4 and
                                             B200CT.
(16) 200T.................................  BT-1 through BT-38 and
                                             B200T.
(17) B200C (C-12F)........................  BL-73 through BL-112 and BL-
                                             118 through BL-123.
(18) B200C (C-12F)........................  BP-64 through BP-71.
(19) B200C (UC-12F).......................  BU-1 through BU-10.
(20) B200C (UC-12M).......................  BV-1 through BV-12.
(21) B200CT...............................  FG-1 and FG-2.
(22) 300..................................  FA-1 through FA-228.
(23) 300..................................  FF-1 through FF-19.
(24) B300.................................  FL-1 through FL-103.
(25) B300C................................  FM-1 through FM-8.
(26) B300C................................  FN-1.
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) As currently written, AD 93-25-07 allows continued flight if 
cracks are found in

[[Page 2943]]

less than five fuselage stringers in the area of the rear pressure 
bulkhead. In 1996, FAA developed policy to not allow airplane 
operation when known cracks exist in primary structure, unless the 
ability to sustain limit and ultimate load with these cracks is 
proven. The fuselage stringers in the area of the rear pressure 
bulkhead are considered primary structure. This AD will bring the 
actions of AD 93-25-07 in compliance with current FAA policy. The 
actions specified in this AD are intended to detect and correct any 
cracked fuselage stringers in the rear pressure bulkhead area, which 
could result in structural damage to the fuselage. This damage could 
lead to failure of the fuselage with potential loss of control of 
the airplane.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) For airplanes that have been   If airplane has    Incorporate the
 known cracks that exist in any    less than five      modification
 of the aft fuselage stringer      known cracked       kit(s) following
 locations (No. 5 through No. 11   stringers: Within   the procedures in
 on both the left-hand and right-  25 cycles after     Raytheon
 hand sides). Either modify or     March 1, 2005       Mandatory Service
 incorporate repairs as            (the effective      Bulletin SB 53-
 specified below. These cracks     date of this AD),   2472, Rev. 4,
 could have been detected          unless already      Issued: June,
 through compliance with AD 93-    done. If cycles     1993, Revised:
 25-07 and/or Raytheon Mandatory   are unknown, then   July, 2003.
 Service Bulletin SB 53-2472,      you may divide      Incorporate the
 any revision level:               hours time-in-      external doubler
(i) Incorporate the applicable     service (TIS) by    repairs following
 modification kit or kits as       .75 (18.75 hours    the procedures in
 specified in Raytheon Mandatory   TIS / .75 = 25      the maintenance
 Service Bulletin SB 53-2472,      cycles). If         manual.
 Rev. 4, Issued: June, 1993,       airplane has five
 Revised: July, 2003; or.          or more known
(ii) Incorporate external          cracked
 doubler repairs on all aft        stringers: Before
 fuselage stringer locations       further flight
 (No. 5 through No. 11 on both     after March 1,
 the left-hand and right-hand      2005 (the
 sides).                           effective date of
                                   this AD), unless
                                   already done. AD
                                   93-35-07 already
                                   required this.
---------------------------------
(2) For all airplanes that do     For airplanes       Inspect following
 not have either the               affected by AD 93-  the procedures in
 modifications or repairs          25-07: Initially    Raytheon
 specified in paragraphs           inspect at the      Mandatory Service
 (e)(1)(i) and (e)(1)(ii) of       next inspection     Bulletin SB 53-
 this AD incorporated in all aft   interval required   2472. Rev. 4,
 fuselage stringer locations       by AD 93-35-07.     Issued: June,
 (No. 5 through No. 11 on both     Repetitively        1993, Revised:
 the left-hand and right-hand      inspect             July, 2003.
 sides): Inspect these aft         thereafter at
 fuselage stringers. If sealant    intervals not to
 covers the stringers, you must    exceed 500
 remove it to facilitate the       cycles. If cycles
 required inspections and then     are unknown, then
 reapplied. You may terminate      you may divide
 the repetitive inspections when   TIS by .75 (375
 all aft fuselage stringer         hours TIS / .75 =
 locations (No. 5 through No. 11   500 cycles). For
 on both the left-hand and right-  airplanes not
 hand sides) are modified.         affected by AD 93-
                                   25-0-7: Initially
                                   inspect upon
                                   accumulating
                                   2,500 cycles on
                                   the fuselage or
                                   within the next
                                   25 cycles after
                                   March 1, 2005
                                   (the effective
                                   date of this AD),
                                   whichever occurs
                                   later, unless
                                   already done.
                                   Repetitively
                                   inspect
                                   thereafter at
                                   intervals not to
                                   exceed 500
                                   cycles. If cycles
                                   are unknown, then
                                   you may divide
                                   hours TIS by .75
                                   (1,875 hours TIS /
                                    .75 = 2,500
                                   cycles; 375 hours
                                   TIS / .75 = 500
                                   cycles; and 18.75
                                   hours TIS / .75 =
                                   25 cycles).
---------------------------------
(3) If any cracks are found       If less than five   Incorporate the
 during any inspection required    cracked stringers   modification
 by this AD, do one of the         are found: Within   kit(s) following
 following:                        25 cycles after     the procedures in
(i) Incorporate the applicable     March 1, 2005       Raytheon
 modification kit or kits as       (the effective      Mandatory Service
 specified in Raytheon Mandatory   date of this AD),   Bulletin SB 53-
 Service Bulletin SB 53-2472,      unless already      2472, Rev. 4,
 Rev. 4, Issued: June, 1993,       done. If cycles     Issued: June,
 Revised: July, 2003; or.          are unknown, then   1993, Revised:
(ii) Incorporate external          you may divide      July, 2003.
 doubler repairs on all aft        hours TIS by .75    Incorporate the
 fuselage stringer locations       (18.75 hours TIS /  external doubler
 (No. 5 through No. 22 on both      .75 = 25           repairs following
 the left-hand and right-hand      cycles). If five    the procedures in
 sides).                           or more cracked     the maintenance
                                   stringers are       manual.
                                   found: Before
                                   further flight
                                   after any
                                   inspection where
                                   five cracked
                                   stringers are
                                   found, unless
                                   already done.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Wichita Aircraft 
Certification Office (ACO), FAA. For information on any already 
approved alternative methods of compliance, contact Steven E. 
Potter, Aerospace Engineer, Wichita Aircraft Certification Office 
(ACO), FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: 
(316) 946-4124; facsimile: (316) 946-4107.

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following the 
instructions in Raytheon Mandatory Service Bulletin SB 53-2472, Rev. 
4, Issued: June, 1993, Revised: July, 2003. The Director of the 
Federal Register approved the incorporation by reference of this 
service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. You may get a copy from Raytheon Aircraft Company, 9709 E. 
Central, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or 
(316) 676-3140. You may review copies at FAA, Central Region, Office 
of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 
64106; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://

[[Page 2944]]

www.archives.gov/federal--register/code--of--federal--regulations/
ibr--locations.html.

    Issued in Kansas City, Missouri, on January 7, 2005.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-716 Filed 1-18-05; 8:45 am]
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