FR Doc 04-20688

[Federal Register: September 14, 2004 (Volume 69, Number 177)]
[Proposed Rules]
[Page 55369-55373]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14se04-17]

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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: 9-ACE-7-Docket@faa.gov. 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?

------------------------------------------------------------------------
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]

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