[Federal Register Volume 69, Number 53 (Thursday, March 18, 2004)]
[Proposed Rules]
[Pages 12807-12810]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-6113]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 69, No. 53 / Thursday, March 18, 2004 /
Proposed Rules
[[Page 12807]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-CE-51-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company 65, 90, 99,
100, 200, and 1900 Series Airplanes, and Models 70 and 300 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 87-
22-01 R1, which applies to certain Raytheon Aircraft Company (Raytheon)
65, 90, 99, 100, 200, and 1900 series airplanes, and Models 70 and 300
airplanes. AD 87-22-01 R1 currently requires you to repetitively
inspect the nose landing gear (NLG) fork for cracks. If cracks are
found that exceed certain limits, AD 87-22-01 R1 requires you to
replace the NLG fork with a serviceable part or an improved NLG fork
(Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as applicable).
Installing an improved NLG fork kit is terminating action for the
repetitive inspection requirements. This proposed AD is the result of
FAA's current policy to disallow airplane operation when known cracks
exist in primary structure. This proposed AD would retain the
inspection requirements of AD 87-22-01 R1 and would require you to
incorporate an improved NLG fork kit anytime a crack is found. We are
issuing this proposed AD to detect and correct cracks in the NLG fork,
which could result in reduced structural integrity and inability of the
NLG fork to carry design limit and ultimate loads. The reduced residual
strength may cause separation failure of the NLG fork, which could
result in loss of control of the airplane during take off, landing, and
taxi operations.
DATES: We must receive any comments on this proposed AD by May 18,
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. 2003-CE-51-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. 2003-CE-51-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. 2003-CE-51-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-
4407.
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. 2003-CE-51-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 in the
nose landing gear (NLG) fork on several Raytheon airplanes caused us to
issue AD 87-22-01, Amendment 39-5748 and AD 87-22-01 R1, Amendment 39-
6312 against certain Raytheon 65, 90, 99, 100, 200, and 1900 series
airplanes, and Models 70 and 300 airplanes.
AD 87-22-01 required you to repetitively inspect the nose landing
gear (NLG) fork for cracks. If cracks were found during any inspection
that exceeded certain limits, you were required to replace the NLG fork
with a serviceable part.
AD 87-22-01 R1 retained the repetitive inspection and replacement
requirements from AD 87-22-01. AD 87-22-01 R1 also introduced
incorporating an improved NLG fork (Kit No. 101-8030-1 S or Kit No.
114-8015-1 S, as applicable) as a terminating action for the repetitive
inspection requirements.
What has happened since AD 87-22-01 R1 to initiate this proposed
action? As currently written, AD 87-22-01 R1 allows continued flight if
cracks are found in the NLG fork that do not exceed certain limits. AD
87-22-01 R1 contradicts the FAA's current policy to disallow airplane
operation when known cracks exist in primary structure, unless the
ability to sustain limit and ultimate load with these cracks is proven.
The NLG fork is considered primary structure, and the FAA has not
received any analysis to prove that limit and ultimate loads can be
sustained with cracks in this area. For this reason, the FAA has
determined that the crack limits contained in AD 87-22-01 R1 should be
eliminated and that AD action should be taken to require immediate
incorporation of Kit No. 101-8030-1 S or Kit No. 114-8015-1 S, as
applicable, anytime a crack is found.
This policy did not exist when we issued AD 87-22-01 and AD 87-22-
01 R1.
What is the potential impact if FAA took no action? This condition,
if not detected and corrected, could cause
[[Page 12808]]
failure of the NLG fork to carry design limit and ultimate loads.
Failure of the NLG fork could result in loss of control of the airplane
during take off, landing, and taxi operations.
Is there service information that applies to this subject? Raytheon
has issued Mandatory Service Bulletin SB 32-2102, Revision 7, Revised:
July, 2003, to remove flight with allowable crack limits.
What are the provisions of this service information? The service
bulletin includes procedures for:
--inspecting the nose landing gear (NLG) fork assembly for cracks; and
--replacing the NLG fork assembly anytime cracks are found.
FAA's 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 87-22-01 R1 with a new AD that would incorporate the
actions in the previously-referenced service bulletin.
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 approximately 5,296 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
accomplish this proposed inspection:
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Total cost
Labor cost Parts cost per airplane Total cost on U.S. operators
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2 workhours x $65 per hour = $130. Not applicable...... $130 $130 x 5,296 = $688,480.
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We estimate the following costs to accomplish any necessary
replacements 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/replacement:
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Labor cost Parts cost Total cost per kit
----------------------------------------------------------------------------------------------------------------
4 workhours x $65 per hour = Kit No. 101-8030- Kit No. 101-8030-1 S: $260 + $4,152 = $4,412.
$260. 1 S = $4,152.
Kit No. 114-8015- Kit No. 114-8015-1 S: $60 + $4,210 = $4,470.
1 S = $4,210.
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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. 2003-CE-51-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) 87-22-01 R1, Amendment 39-6312 and by adding a new AD to read as
follows:
Raytheon Aircraft Company: Docket No. 2003-CE-51-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 May 18, 2004.
What Other ADs Are Affected by This Action?
(b) This AD supersedes AD 87-22-01 R1, Amendment 39-6312.
What Airplanes Are Affected by This AD?
(c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
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Model Serial Nos.
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(1) A65 and A65-8200................... LC-240 through LC-335.
(2) 70................................. LB-1 through LB-35.
(3) 65-A80, 65-A80-8800, and 65-B80.... LD-151 through LD-511.
(4) 65-88.............................. LP-1 through LP-26, LP-28, and
LP-30 through LP-47.
(5) 65-90, 65-A90, B90, C90, and C90A.. LJ-1 through LJ-1190.
[[Page 12809]]
(6) 65-A90-1 (U-21A, JU-21A, U-21G, RU- LM-1 through LM-141.
21A, RU-21D, and RU-21H).
(7) 65-A90-2 (RU-21B).................. LS-1 through LS-3.
(8) 65-A90-3 (RU-21C).................. LT-1 and LT-2.
(9) 65-A90-4 (RU-21E and RU-21H)....... LU-1 through LU-15.
(10) E90............................... LW-1 through LW-347.
(11) F90............................... LA-2 through LA-236.
(12) H90 (T-44A)....................... LL-1 through LL-61.
(13) 99, 99A, A99, A99A, B99, and C99.. U-1 through U-239.
(14) 100 and A100...................... B-2 through B-93, and B-100
through B-247.
(15) A100 (U-21F)...................... B-95 through B-99.
(16) A100-1 (U-21J).................... BB-3 through BB-5.
(17) B100.............................. BE-1 through BE-137.
(18) 200 and B200...................... BB-2, and BB-6 through BB-1314.
(19) 200C and B200C.................... BL-1 through BL-72, and BL-124
through BL-131.
(20) 200CT and B200CT.................. BN-1 through BN-4.
(21) 200T and B200T.................... BT-1 through BT-33.
(22) A200 (C-12A and C-12C)............ BC-1 through BC-75 and BD-1
through BD-30.
(23) A200C (UC-12B).................... BJ-1 through BJ-66.
(24) A200CT (C-12D, FWC-12D, and C-12F) BP-1, BP-7 through BP-11, BP-
19, and BP-24 through BP-63.
(25) A200CT (RC-12D and RC-12H)........ GR-1 through GR-19.
(26) A200CT (RC-12G)................... FC-1 through FC-3.
(27) A200CT (RC-12K)................... FE-1 through FE-9.
(28) B200C (C-12F)..................... BL-73 through BL-112, BL-118
through BL-123, and BP-64
through BP-71.
(29) B200C (UC-12F).................... BU-1 through BU-10.
(30) B200C (UC-12M).................... BV-1 through BV-10.
(31) 300............................... FA-1 through FA-168, and FF-1
through FF-19.
(32) 1900.............................. UA-1 through UA-3.
(33) 1900C............................. UB-1 through UB-74, and UC-1
through UC-78.
(34) 1900C (C-12J)..................... UD-1 through UD-6.
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What Is the Unsafe Condition Presented in This AD?
(d) The actions specified in this AD are intended to detect and
correct cracks in the nose landing gear (NLG) fork, which could
result in reduced structural integrity and failure of the NLG fork
to carry design ultimate load. This failure could result in loss of
control of the airplane during take off, landing, and taxi
operations.
What Must I do To Address This Problem?
(e) To address this problem, you must do the following:
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Actions Compliance Procedures
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(1) Inspect, using fluorescent For airplanes Follow the
liquid penetrant or magnetic affected by AD 87- instructions in
particle method, the nose 22-01 R1: Part II of
landing gear (NLG) fork Initially inspect Raytheon Aircraft
assembly for any signs of within 200 hours Company Mandatory
cracks. time-in-service Service Bulletin
(TIS) after the SB 32-2102,
last inspection Revision 7,
required by AD 87- Revised: July,
22-01 R1. For 2003.
airplanes not
affected by AD 87-
22-01 R1:
Initially inspect
within the next
200 hours TIS
after the
effective date of
this AD, unless
already done.
(2) If cracks are found during Before further Follow the
the inspection required in flight after the instructions in
paragraph (e)(1) of this AD, effective date of Part III of
incorporate Kit No. 101-8030-1 this AD. Raytheon Aircraft
S or Kit No. 114-8015-1 S (as Company Mandatory
applicable). Service Bulletin
SB 32-2102,
Revision 7,
Revised: July,
2003.
(3) If no cracks are found Repetitively Follow the
during the inspection required inspect at instructions in
in paragraph (e)(1) of this AD, intervals not to Part III of
repetitively inspect until Kit exceed 200 hours Raytheon Aircraft
No. 101-8030-1 S or Kit No. 114- TIS after the Company Mandatory
8015-1 S (as applicable) is initial Service Bulletin
incorporated. When Kit No. 101- inspection. SB 32-2102,
8030-1 S or Kit No. 114-8015-1 Incorporate Kit Revision 7,
S is incorporated, no further No. 101-8030-1 S Revised: July,
action is required. or Kit No. 114- 2003.
8015-1 S (as
applicable) prior
to further flight
after any
inspection in
which cracks are
found.
(4) Incorporating Kit No. 101- Kit No. 101-8030-1 Follow Raytheon
8030-1 S or Kit No. 114-8015-1 S or Kit No. 114- Aircraft Company
S (as applicable) is the 8015-1 S (as Mandatory Service
terminating action for the applicable) can Bulletin SB 32-
repetitive inspection be incorporated 2102, Revision 7,
requirements specified in at any time. When Revised: July,
paragraph (e)(3) of this AD. incorporated, no 2003.
further action is
required.
------------------------------------------------------------------------
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 ACO, FAA, 1801 Airport Road,
[[Page 12810]]
Wichita, Kansas 67209; telephone: (316) 946-4124; facsimile: (316)
946-4407.
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 March 12, 2004.
Scott L. Sedgwick,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-6113 Filed 3-17-04; 8:45 am]
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