[Federal Register Volume 69, Number 177 (Tuesday, September 14, 2004)]
[Proposed Rules]
[Pages 55369-55373]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20688]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-CE-01-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (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 
proposed 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

[[Page 55370]]

considered primary structure and operation is currently allowed for a 
certain period of time if less than five fuselage stringers are 
cracked. Consequently, this proposed AD would retain the inspection and 
modification requirements of AD 93-25-07, but would require you to 
repair any cracked fuselage stringers. We are issuing this proposed 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: We must receive any comments on this proposed AD by November 2, 
2004.

ADDRESSES: Use one of the following to submit comments on this proposed 
AD:
     By mail: FAA, Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2004-CE-01-AD, 901 Locust, Room 
506, Kansas City, Missouri 64106.
     By fax: (816) 329-3771.
     By e-mail: [email protected]. Comments sent 
electronically must contain ``Docket No. 2004-CE-01-AD'' in the subject 
line. If you send comments electronically as attached electronic files, 
the files must be formatted in Microsoft Word 97 for Windows or ASCII.
    You may get the service information identified in this proposed 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:

Comments Invited

    How do I comment on this proposed AD? We invite you to submit any 
written relevant data, views, or arguments regarding this proposal. 
Send your comments to an address listed under ADDRESSES. Include ``AD 
Docket No. 2004-CE-01-AD'' in the subject line of your comments. If you 
want us to acknowledge receipt of your mailed comments, send us a self-
addressed, stamped postcard with the docket number written on it. We 
will date-stamp your postcard and mail it back to you.
    Are there any specific portions of this proposed AD I should pay 
attention to? We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of this 
proposed AD. If you contact us through a nonwritten communication and 
that contact relates to a substantive part of this proposed AD, we will 
summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend this 
proposed AD in light of those comments and contacts.

Discussion

    Has FAA taken any action to this point? 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 proposed 
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 proposed AD would bring 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.
    Is there service information that applies to this subject? Raytheon 
has issued Mandatory Service Bulletin SB 53-2472, Rev. 4, Revised: 
July, 2003.
    What are the provisions of this service information? The service 
bulletin includes procedures for:

--Inspecting the fuselage stringers (Nos. 5 through 11) in the rear 
pressure bulkhead for cracks; and
--Incorporating a modification kit on any cracked fuselage stringer.

Determination and Requirements of This Proposed AD

    What has FAA decided? We have evaluated all pertinent information 
and identified an unsafe condition that is likely to exist or develop 
on other products of this same type design. Therefore, we are proposing 
AD action.
    What would this proposed AD require? This proposed AD would 
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. The FAA is 
proposing 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. The specific Raytheon Beech 
airplane models affected by this AD are as follows:

------------------------------------------------------------------------
                   Model                             Serial Nos.
------------------------------------------------------------------------
A100-1 (U-21J)............................  BB-3 through BB-5.
200 and B200..............................  BB-2 and BB-6 through BB-
                                             1462.
A200 (C-12A) and A200 (C-12C).............  BC-1 through BC-75 and BD-1
                                             through BD-30.
A200C (UC-12B)............................  BJ-1 through BJ-66.
A200CT (C-12D)............................  BP-1, BP-22, and BP-24
                                             through BP-51.
A200CT (FWC-12D)..........................  BP-7 through BP-11.
A200CT (RC-12D)...........................  GR-1 through GR-13.
A200CT (C-12F)............................  BP-52 through BP-63.
A200CT (RC-12G)...........................  FC-1 and FC-3.
A200CT (RC-12H)...........................  GR-14 through GR-19.
A200CT (RC-12K)...........................  FE-1 through FE-9.

[[Page 55371]]

 
A200CT (RC-12P)...........................  FE-10 through FE-24.
A200CT (RC-12K)...........................  FE-25 through FE-31.
200C and B200C............................  BL-1 through BL-72 and BL-
                                             124 through BL-138.
200CT and B200CT..........................  BN-1 through BN-4.
B200T and 200T............................  BT-1 through BT-38.
B200C (C-12F).............................  BL-73 through BL-112 and BL-
                                             118 through BL-123.
B200C (C-12F).............................  BP-64 through BP-71.
B200C (UC-12F)............................  BU-1 through BU-10.
B200C (UC-12M)............................  BV-1 through BV-12.
B200CT....................................  FG-1 and FG-2.
300.......................................  FA-1 through FA-228.
300.......................................  FF-1 through FF-19.
B300......................................  FL-1 through FL-103.
B300C.....................................  FM-1 through FM-8.
B300C.....................................  FN-1.
------------------------------------------------------------------------

    How does the revision to 14 CFR part 39 affect this proposed AD? On 
July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs 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 would this proposed AD impact? We estimate that 
this proposed AD affects 2,300 airplanes in the U.S. registry.
    What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to 
do each proposed inspection:

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

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

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

Regulatory Findings

    Would this proposed AD impact various entities? We have determined 
that this proposed AD would not have federalism implications under 
Executive Order 13132. This proposed AD 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.
    Would this proposed AD involve a significant rule or regulatory 
action? For the reasons discussed above, I certify that this proposed 
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 proposed 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, 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 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. 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:

Raytheon Aircraft Company: Docket No. 2004-CE-01-AD.

When Is the Last Date I Can Submit Comments on This Proposed AD?

    (a) We must receive comments on this proposed airworthiness 
directive (AD) by November 2, 2004.

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.

[[Page 55372]]

 
(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 and B200CT.....................  BN-1 through BN-4.
(16) 200T and B200T.......................  BT-1 through BT-38.
(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 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 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   If airplane has than  Incorporate the
 known cracks that exist in    five known cracked    modification kit(s)
 any of the aft fuselage       stringers: Within     following the
 stringer locations (No. 5     25 cycles after the   procedures in
 through No. 11 on both the    effective date of     Raytheon Mandatory
 left-hand and right-hand      this AD, unless       Service Bulletin SB
 sides). Either modify or      previously done. If   53-2472, Rev. 4,
 incorporate repairs as        cycles are unknown,   Issued: June, 1993,
 specified below. These        then you may divide   Revised: July,
 cracks could have been        hours time-in-        2003, Incorporate
 detected through compliance   service (TIS) by      the external
 with AD 93-25-07 and/or       .75 (18.75 hours      doubler repairs
 Raytheon Mandatory Service    TIS / .75 = 25        following the
 Bulletin SB 53-2472, any      cycles). If           procedures in the
 revision level:               airplane has five     maintenance manual.
(i) Incorporate the            or more known
 applicable modification kit   cracked stringers:
 or kits as specified in       Prior to further
 Raytheon Mandatory Service    flight after the
 SB 53-2472, Rev. 4, Issued:   effective date of
 June, 1993, Revised: 1993,    this AD, unless
 Revised: July, 2003; or.      previously done. AD
(ii) Incorporate external      93-25-07 already
 doubler repairs on all aft    required this.
 fuselage stringer locations
 (No. 5 through No. 11 on
 both the left-hand and
 right-hand sides)..
(2) For all airplanes that    For airplanes         Inspect following
 do not have either the        affected by AD 93-    the procedures in
 modifications or repairs      25-07: Initially      Raytheon Mandatory
 specified in paragraphs       inspect at the next   Service Bulletin SB
 (e)(1)(i) and (e)(1)(ii) of   inspection interval   53-2472, Rev. 4,
 this AD incorporated in all   required by AD 93-    Issued: June, 1993,
 aft fuselage stringer         25-07. Repetitively   Revised: July 2003.
 locations (No. 5 through      inspect thereafter
 No. 11 on both the left-      at intervals not to
 hand and right-hand sides):   exceed 500 cycles.
 Inspect these aft fuselage    If cycles are
 stringers. You may            unknown, then you
 terminate the repetitive      may divide hours
 inspections when all aft      time-in-service
 fuselage stringer locations   (TIS) by .75 (375
 (No. 5 through No. 11 on      hours TIS / .75 =
 both the left-hand and        500 cycles). For
 right-hand sides) are         airplanes not
 modified.                     affected by AD 93-
                               25-07: Initially
                               inspect upon
                               accumulating 2,500
                               cycles on the
                               fuselage or within
                               the next 25 cycles
                               after the effective
                               date of this AD,
                               whichever occurs
                               later, unless
                               previously done.
                               Repetitively
                               inspect thereafter
                               at intervals not to
                               exceed 500 cycles.
                               If cycles are
                               unknown, then you
                               may divide hours
                               time-in-service
                               (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         cracked stringers     modification kit(s)
 required by this AD, do one   are found: Within     following the
 of the following:             25 cycles after the   procedures in
(i) Incorporate the            effective date of     Raytheon Mandatory
 applicable modification kit   this AD, unless       Service Bulletin SB
 or kits as specified in       previously done. If   53-2472, Rev. 4,
 Raytheon Mandatory Service    cycles are unknown,   Issued: June, 1993,
 Bulletin SB 53-2472, Rev.     then you may divide   Revised: July,
 4, Issued: June, 1993,        hours time-in-        2003. Incorporate
 Revised: July, 2003; or.      service (TIS) by      the external
(ii) Incorporate external      .75 (18.75 hours      doubler repairs
 doubler repairs on all aft    TIS / .75 = 25        following the
 fuselage stringer locations   cycles). If five or   procedures in the
 (No. 5 through No. 11 on      more cracked          maintenance manual.
 both the left-hand and        stringers are
 right-hand sides)..           found: Prior to
                               further flight
                               after any
                               inspection where
                               five cracked
                               stringers are
                               found, unless
                               previously 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,

[[Page 55373]]

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.

May I Get Copies of the Documents Referenced in This AD?

    (g) You may get copies of the documents referenced 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 these documents at FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

    Issued in Kansas City, Missouri, on September 8, 2004.
Dorenda D. Baker,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-20688 Filed 9-13-04; 8:45 am]
BILLING CODE 4910-13-P