FR Doc 05-716

[Federal Register: January 19, 2005 (Volume 70, Number 12)]
[Rules and Regulations]
[Page 2941-2944]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19ja05-4]

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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..
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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?

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

[[Page 2944]]

http://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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