[Federal Register: March 1, 2004 (Volume 69, Number 40)]
[Rules and Regulations]
[Page 9526-9529]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01mr04-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-CE-09-AD; Amendment 39-13496; AD 2001-13-18 R1]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Corporation Beech
Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is revising Airworthiness Directive (AD) 2001-13-18,
which applies to Raytheon Aircraft Corporation (Raytheon) Beech Models
45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) airplanes. AD 2001-13-18
currently requires you to repetitively inspect the wing spar assembly
for cracks and replace any wing spar assembly found cracked (unless the
spar assembly has a crack indication in the filler strip where the
direction of the crack is toward the outside edge of the filler strip).
AD 2001-13-18 also requires you to report the results of the initial
inspection and maintain the flight and operating restrictions required
by AD 99-12-02 until the initial inspection is done. We approved
alternative methods of compliance (AMOCs) to AD 2001-13-18. We have
since determined that those AMOCs do not address all critical areas in
the wing spar assemblies and should no longer be valid. We are issuing
this revision to AD 2001-13-18 for the purpose of eliminating the AMOCs
to AD 2001-13-18. The actions of this AD are intended to prevent wing
spar failure caused by fatigue cracks in the wing spar assemblies and
ensure the operational safety of the above-referenced airplanes.
DATES: This AD becomes effective on March 15, 2004.
On August 16, 2001 (66 FR 34802, July 2, 2001), the Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulation.
We must receive any comments on this AD by April 26, 2004.
ADDRESSES: Use one of the following to submit comments on this AD:
By mail: FAA, Central Region, Office of the
Regional Counsel,
[[Page 9527]]
Attention: Rules Docket No. 2000-CE-09-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. 2000-CE-09-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 AD from
Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085;
telephone: (800) 625-7043 or (316) 676-4556.
You may view the AD docket at FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2000-CE-09-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: Paul Nguyen, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent
Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile:
(316) 946-4107.
SUPPLEMENTARY INFORMATION:
Has FAA Taken Any Action to This Point?
In-flight separation of the right wing on a Raytheon Beech Model
A45 (T34A) airplane caused FAA to issue AD 99-12-02, Amendment 39-11193
(64 FR 31689, June 14, 1999) against Raytheon Beech Models 45 (YT-34),
A45 (T-34A, B-45), and D45 (T-34B) airplanes. This AD requires:
--Incorporating flight and operating limitations that restrict the
airplanes to normal category operation and prohibit them from acrobatic
and utility category operations;
--Limiting the flight load factor to 0 to 2.5 G; and
--Limiting the maximum airspeed to 175 miles per hour (mph) (152
knots).
AD 99-12-02 was issued as an interim action until the development
of FAA-approved inspection procedures.
Those procedures were developed and FAA superseded AD 99-12-12 with
AD 2001-13-18, Amendment 39-12300 (66 FR 34802, July 2, 2001). AD 2001-
13-18 contains the following provisions:
--Requires you to repetitively inspect the wing spar assemblies for
cracks and replace any cracked wing spar assembly. A crack indication
in the filler strip is allowed if the direction of the crack is toward
the outside edge of the filler strip;
--Requires you to report the results of the initial inspection;
--Requires you to maintain the flight and operating restrictions that
AD 99-12-02 currently requires until you do the initial inspection and
possible replacement specified in this AD; and
--Allows you to change the flight and operating restrictions that AD
99-12-02 currently requires after the wing spar assemblies are
inspected and the wing spar assembly either is replaced, is crack free,
or only has a crack indication in the filler strip where the direction
of the crack is toward the outside of the filler strip.
You are required to do the inspections of AD 2001-13-18 following
the procedures of Raytheon Mandatory Service Bulletin No. SB 57-3329,
Issued: February, 2000.
What Has Happened Since AD 2001-13-18 To Initiate This AD Action?
In November 2003, a Raytheon Beech Model A45 (T34A) airplane
crashed after the right wing failed at Wing Station (WS) 34 on the
forward spar and WS 66.00 on the rear spar. AD 2001-13-18 was
established to inspect the wing spar assemblies at four locations:
1. Nine fasteners at the WS 34 forward spar.
2. The lower rear bathtub fitting.
3. One fastener at WS 64 on the forward spar.
4. Two fasteners at WS 66.00 on the rear spar.
The FAA has approved and issued different alternative methods of
compliance (AMOCs) for the inspections of AD 2001-13-18. These AMOCs
consist of a combination of modifications and inspections to address
the condition.
None of the AMOCs issued under AD 2001-13-18 address all four
locations of the wing spar assemblies.
FAA's Determination and Requirements of This AD
What Has FAA Decided?
We have evaluated all pertinent information including all
information from the November 2003 accident and determined that the
AMOCs approved under AD 2001-13-18 do not address all critical areas in
the wing spar assemblies and should no longer be valid in order to
prevent wing spar failure caused by fatigue cracks in the wing spar
assemblies and ensure the operational safety of the above-referenced
airplanes.
Therefore, we have determined that AD 2001-13-18 should be revised
for the purpose of eliminating the AMOCs to AD 2001-13-18.
What Does This AD Require?
This AD revises AD 2001-13-18 by retaining all actions (including
compliance times) of AD 2001-13-18, but not retaining the AMOCs
approved through that AD. The requirements of the actual AD portion of
AD 2001-13-18 will remain the same.
In preparing this rule, we contacted type clubs and aircraft
operators to get technical information and information on operational
and economic impacts. We did not receive any information through these
contacts. If received, we would have included a discussion of any
information that may have influenced this action in the rulemaking
docket.
How Does the Revision to 14 CFR Part 39 Affect This 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.
Comments Invited
Will I Have the Opportunity To Comment Before You Issue the Rule?
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2000-CE-09-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. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the rule
that might suggest a need to modify it. If a person contacts us through
a nonwritten communication, and that contact relates to a substantive
part of this 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 the AD in light of those comments.
[[Page 9528]]
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. 2000-CE-09-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)
2001-13-18, Amendment 39-12300 (66 FR 34802, July 2, 2001), and by
adding a new AD to read as follows:
2001-13-18 R1 Raytheon Aircraft Company: Amendment 39-13496; Docket
No. 2000-CE-09-AD; Revises AD 2001-13-18, Amendment 39-12300.
When Does This AD Become Effective?
(a) This AD becomes effective on March 15, 2004.
What Airplanes Are Affected by This AD?
(b) This AD applies to Beech Models 45 (YT-34), A45 (T-34A, B-
45), and D45 (T-34B) airplanes, all serial numbers, that are
certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(c) We are issuing this AD to detect and correct cracks in the
wing spar assemblies and ensure the operational safety of the above-
referenced airplanes.
What Must I Do To Address This Problem?
(d) To address this problem, you must maintain the actions of AD
99-12-02 that are outlined in paragraphs (d)(1), (d)(2), and (d)(3)
of this AD, including all subparagraphs, until you accomplish the
initial inspection required in paragraph (d)(5) of this AD
(paragraphs (d)(1) through (d)(4) are actions retained from AD 99-
12-02, and paragraphs (d)(5) through (d)(7) are actions new to this
AD):
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Action When In accordance with
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(1) Accomplish the following All actions required Not Applicable.
placard requirements: prior to further
flight after July
9, 1999 (the
effective date of
AD 99-12-02),
unless already
accomplished.
(i) Fabricate two placards
using letters of at least
\1/10\-inch in height with
each consisting of the
following words:
``Never exceed speed, Vne-
175 MPH (152 knots) IAS;
Normal Acceleration (G)
Limits--0, and +2.5;
ACROBATIC MANEUVERS
PROHIBITED.''
(ii) Install these placards
on the airplane instrument
panels (one on the front
panel and one on the rear
panel) next to the airspeed
indicators within the
pilot's clear view.
(iii) Insert a copy of this
AD into the Limitations
Section of the Airplane
Flight Manual (AFM).
(2) Modify each airspeed All actions required Not Applicable.
indicator glass by within 10 hours (i) Place a red
accomplishing the time-in-service radial line on each
following: (TIS) after July 9, indicator glass at
1999 (the effective 175 miles per hour
date of AD 99-12- (mph) (152 knots).
02), unless already
accomplished.
(ii) Place a white slippage
index mark between each
airspeed indicator glass
and case to visually verify
that the glass has not
rotated.
(3) Mark the outside surface All actions required Not Applicable.
of the ``g'' meters with within 10 hours
lines of approximately \1/ time-in-service
16\-inch by \3/16\-inch, as (TIS) after July 9,
follows: 1999 (the effective
date of AD 99-12-
02), unless already
accomplished.
(i) A red line at 0 and 2.5;
and
(ii) A white slippage mark
between each ``g'' meter
glass and case to visually
verify that the glass has
not rotated.
(4) The actions required by Upon accomplishment Raytheon Aircraft
paragraphs (d)(1), (d)(2), of the initial Mandatory Service
and (d)(3) are no longer inspection required Bulletin No. SB 57-
required after the initial in paragraph (d)(5) 3329, Issued:
inspection required in of this AD, unless February, 2000.
paragraph (d)(5) of this AD already
is accomplished. accomplished.
[[Page 9529]]
(5) Inspect the wing spar Initially inspect Raytheon Aircraft
assemblies for cracks. within the next 80 Mandatory Service
hours time-in- Bulletin No. SB 57-
service (TIS) after 3329, Issued:
August 16, 2001 February, 2000.
(the effective date
of AD 2001-13-18)
or within 12 months
after August 16,
2001 (the effective
date of AD 2001-13-
18), whichever
occurs later,
unless already
accomplished.
Inspect thereafter
at intervals not to
exceed 80 hours TIS.
(6) Replace any cracked wing Prior to further The applicable
spar assembly. A crack flight after the maintenance manual.
indication in the filler required inspection
strip is allowed if the where the cracked
direction of the crack is wing spar assembly
toward the outside edge of is found.
the filler strip. If the
direction of the crack is
toward the inside edge of
the filler strip or any
crack is found in any other
area, you must replace the
cracked wing spar assembly.
(7) Submit a report to FAA Within 10 days after Pages 58 through 60
that describes the damage the initial of Raytheon
found on the wing spar. Use inspection or Aircraft Mandatory
the chart on pages 58 within 10 days Service Bulletin
through 60 of Raytheon after August 16, No. SB 57-3329,
Aircraft Mandatory Service 2001 (the effective Issued: February,
Bulletin No. SB 57-3329, date of AD 2001-13- 2000.
Issued: February, 2000. 18), whichever
occurs later,
unless already
accomplished.
(i) Submit this report even
if no cracks are found.
(ii) Submit this report to
FAA at the address found in
paragraph (g) of this AD.
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Are Any Other ADs Affected by This Action?
(e) This AD revises AD 2001-13-18, Amendment 39-12300.
What About Alternative Methods of Compliance?
(f) As of March 15, 2004 (the effective date of this AD), all
alternative methods of compliance approved under AD 2001-13-18 are
not approved for this AD and are no longer valid. Any alternative
method of compliance must reference ``AD 2001-13-18 R1'' in order to
be valid.
(g) 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 for this AD, contact Paul
Nguyen, Aerospace Engineer, FAA, Wichita Aircraft Certification
Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas
67209; telephone: (316) 946-4125; facsimile: (316) 946-4107.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the
instructions in Raytheon Aircraft Mandatory Service Bulletin No. SB
57-3329, Issued: February, 2000. On August 16, 2001 (66 FR 34802,
July 2, 2001), the Director of the Federal Register previously
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, P.O. Box 85, Wichita, Kansas
67201-0085; telephone: (800) 625-7043 or (316) 676-4556. You may
review copies at FAA, Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
Issued in Kansas City, Missouri, on February 23, 2004.
Dorenda D. Baker,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-4372 Filed 2-27-04; 8:45 am]
BILLING CODE 4910-13-P