Airworthiness Directives; Raytheon Aircraft Company Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes, 16990-16998 [07-1715]
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16990
Federal Register / Vol. 72, No. 66 / Friday, April 6, 2007 / Rules and Regulations
4. Projected reporting, recordkeeping,
and other compliance requirements.
There are no reporting, recordkeeping,
or other compliance requirements
associated with the revised
Interpretation.
5. Minimizing significant economic
impact of the revised Interpretation on
small entities. There were no public
comments that suggested a significant
alternative that would minimize the
impact of the proposal on small entities.
There are eleven bankers’ banks
qualifying as ‘‘small entities’’ under
RFA. The revised Interpretation
provides all bankers’ banks with the
ability to maintain their exemption from
reserve requirements, if any, while
undertaking certain additional bankers’
bank activities or customers as
authorized by their chartering
authorities. No bankers’ bank is required
to seek a determination under the
revised Interpretation. The revised
Interpretation imposes no economic
burdens on bankers’ banks, and instead
only offers the opportunity to bankers’
banks that are exempt from reserve
requirements to maintain the economic
benefits of that exemption under the
specified circumstances. Accordingly,
the Board believes that the revised
Interpretation will not have a significant
impact on a substantial number of small
entities.
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B. Paperwork Reduction Act
In accordance with the Paperwork
Reduction Act (PRA) of 1995 (44 U.S.C.
3506; 5 CFR part 1320 Appendix A.10),
the Board reviewed the proposal under
the authority delegated to the Board by
the Office of Management and Budget
(OMB). The proposal contains no
requirements subject to the PRA.
VI. Plain Language
The Board received one comment on
whether the proposal was in plain
language. This commenter stated that
the Board’s failure to propose standards
for its exercise of authority under the
proposal amounted to a failure to
comply with the ‘‘Plain Language’’
provisions of the Gramm-Leach-Bliley
act. This commenter stated that the
Board should instead say that it
proposes to do whatever it wants given
its view of the purposes of the Act. For
the reasons stated above, the Board
believes that the revised Interpretation
is stated in plain language to the greatest
extent possible at this point in time. As
also stated above, the Board expects to
publish further guidance and standards
as it obtains additional experience in
the future with requests for
determinations under the revised
Interpretation. Accordingly, the Board
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believes that the revised Interpretation
complies with applicable plain language
requirements.
DEPARTMENT OF TRANSPORTATION
List of Subjects in 12 CFR Part 204
14 CFR Part 39
Banks, banking, Reporting and
recordkeeping requirements.
For the reasons set forth in the
preamble, the Board is amending 12
CFR part 204 as follows:
I
PART 204—RESERVE
REQUIREMENTS OF DEPOSITORY
INSTITUTIONS (REGULATION D)
1. The authority citation for part 204
continues to read as follows:
I
Authority: 12 U.S.C. 248(a), 248(c), 371a,
461, 601, 611, and 3105.
2. The second sentence of paragraph
(a)(2)(iii) of § 204.121 is revised to read
as follows:
I
§ 204.121
Bankers’ banks.
(a) * * *
(2) * * *
(iii) * * * First, the range of
customers with which the institution
does business must be limited to
depository institutions, including
subsidiaries or organizations owned by
depository institutions; directors,
officers or employees of the same or
other depository institutions;
individuals whose accounts are
acquired at the request of the
institution’s supervisory authority due
to the actual or impending failure of
another depository institution; share
insurance funds; depository institution
trade associations; and such others as
the Board may determine on a case-bycase basis consistent with the purposes
of the Act and the bankers’ bank
exemption. * * *
*
*
*
*
*
By order of the Board of Governors of the
Federal Reserve System, April 3, 2007.
Jennifer J. Johnson,
Secretary of the Board.
[FR Doc. E7–6473 Filed 4–5–07; 8:45 am]
BILLING CODE 6210–02–P
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Federal Aviation Administration
[Docket No. FAA–2006–25105; Directorate
Identifier 2006–CE–33–AD; Amendment 39–
15016; AD 2007–06–01 R1]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Aircraft Company Beech Models 45
(YT–34), A45 (T–34A, B–45), and D45
(T–34B) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
SUMMARY: We are clarifying information
contained in Airworthiness Directive
(AD) 2007–06–01, which supersedes AD
62–24–01 and applies to all Raytheon
Aircraft Company (RAC) Beech Models
45 (YT–34), A45 (T–34A, B45), and D45
(T–34B) airplanes. AD 2007–06–01
currently requires you to repetitively
inspect, using the eddy current method,
the front and rear horizontal stabilizer
spars for cracks and replace any cracked
stabilizer. We inadvertently left out the
language in this AD that required
replacement of any horizontal stabilizer
spar found cracked prior to further flight
although the procedures in the
appendix made reference to corrective
action. The replacement information
was contained in the notice of proposed
rulemaking (NPRM). This document
adds this information already proposed
back into the AD. We are issuing this
AD to prevent failure of the front and/
or rear horizontal stabilizer spars caused
by fatigue cracks. This failure could
result in stabilizer separation and loss of
control of the airplane.
DATES: This AD becomes effective on
April 16, 2007.
ADDRESSES: To view the AD docket, go
to the Docket Management Facility, U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2006–25105; Directorate Identifier
2006–CE–33–AD.
FOR FURTHER INFORMATION CONTACT: T.N.
Baktha, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office,
1801 Airport Road, Mid-Continent
Airport, Wichita, Kansas 67209;
telephone: (316) 946–4155; fax: (316)
946–4107.
SUPPLEMENTARY INFORMATION:
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Discussion
List of Subjects in 14 CFR Part 39
On March 5, 2007, we issued AD
2007–06–01, Amendment 39–14982 (72
FR 10909, March 12, 2007), to supersede
AD 62–24–01. AD 2007–06–01 retained
inspections of the front and rear
horizontal stabilizer spars for cracks, but
changed the inspection method from the
dye penetrant method to the surface
eddy current method.
We inadvertently left out the language
in AD 2007–06–01 that required
replacement of any horizontal stabilizer
spar found cracked prior to further flight
although the procedures in the
appendix made reference to corrective
action. The replacement information
was contained in the NPRM.
Consequently, the FAA sees a need to
clarify AD 2007–06–01 to assure that
any cracked horizontal stabilizer spar is
replaced prior to further flight.
Air transportation, Aircraft, Aviation
safety, Safety.
Correction of Publication
This document clarifies AD 2007–06–
01 by incorporating the replacement
language that was proposed in the
NPRM and adds the amendment to
section 39.13 of the Federal Aviation
Regulations (14 CFR 39.13).
Since this action only clarifies the
intent of what was originally proposed
in the NPRM, it has no adverse
economic impact and imposes no
additional burden on any person than
was already proposed. Therefore, the
FAA has determined that prior notice
and opportunity for public comment are
unnecessary.
Adoption of the Amendment
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2007–06–01, Amendment 39–14982 (72
FR 10909, March 12, 2007), and adding
the following new AD:
I
2007–06–01 R1 Raytheon Aircraft
Company: Amendment 39–15016;
Docket No. FAA–2006–25105;
Directorate Identifier 2006–CE–33–AD.
Effective Date
(a) This AD becomes effective on April 16,
2007.
Affected ADs
(b) This AD revises AD 2007–06–01,
Amendment 39–14982, which superseded
AD 62–24–01, Amendment 39–508.
Applicability
(c) This AD affects the following airplane
models and serial numbers that are
certificated in any category:
Model
Beech 45 (YT–34) ...........................
Beech A45 (T34A, B–45) ................
Beech D45 (T–34B) ........................
16991
Serial
Nos.
All.
All.
All.
Unsafe Condition
(d) This AD is intended to prevent failure
of the front and/or rear horizontal stabilizer
spars caused by fatigue cracks by changing
the inspection method from dye penetrant to
surface eddy current. This failure could
result in stabilizer separation and loss of
control of the airplane.
Compliance
(e) Using the surface eddy current
inspection procedures outlined in the
appendix of this AD, inspect the front and
rear horizontal stabilizer spars between the
butt rib and the inboard end for cracks,
unless already done, as presented below. If
any crack is found in either spar or the
reinforcing doubler during any inspection
required by this AD, prior to further flight,
replace the stabilizer and continue to
repetitively inspect at intervals not to exceed
500 hours time-in-service (TIS).
(1) If the last inspection of the front and
rear horizontal stabilizer spars was done
using the surface eddy current method (or
FAA-approved equivalent method) to show
compliance with AD 62–24–01 and/or to
show compliance with the alternative method
of compliance (AMOC) to AD 2004–25–51:
Repetitively inspect thereafter at intervals not
to exceed 500 hours TIS.
(2) If the last inspection of the front and
rear horizontal stabilizer spars required by
AD 62–24–01 was done using the dye
penetrant method: Inspect initially as
presented in the table below and repetitively
thereafter at intervals not to exceed 500 hours
TIS:
If
Then
(i) Less than 200 hours TIS have passed since
the last inspection required by AD 62–24–01:
Inspect at whichever of the following occurs later:
(A) Upon accumulating 200 hours TIS since the last inspection required by AD 62–24–01;
or
(B) Within the next 6 months after April 16, 2007 (the effective date of this AD).
Inspect at whichever of the following occurs first, unless paragraph (e)(2)(iii) of this AD applies, as specified below:
(A) At the next repetitive inspection required by AD 62–24–01; or
(B) Within the next 6 months after April 16, 2007 (the effective date of this AD).
Inspect within the next 30 days after April 16, 2007 (the effective date of this AD).
(ii) 200 hours TIS or more have passed since
the last inspection required by AD 62–24–01:
(iii) Paragraph (e)(2)(ii) results in the initial surface eddy current inspection becoming mandatory within 30 days after the effective date
of this AD:
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Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Wichita Aircraft
Certification Office, FAA, ATTN: T.N.
Baktha, Aerospace Engineer, 1801 Airport
Road, Mid-Continent Airport, Wichita,
Kansas 67209; telephone: (316) 946–4155;
fax: (316) 946–4107, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 62–24–01 are
approved for this AD.
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Appendix to AD 2007–06–01 R1—
Surface Eddy Current Inspection
Procedure
Certification Office and requested using the
procedures found in 14 CFR 39.19.
Note: This surface eddy current inspection
procedure is based on T–34 Spar Corporation
TSC 3506, Rev C, dated May 10, 2005. The
T–34 Spar Corporation is allowing the use of
this procedure to be included in this
Airworthiness Directive. Alternative methods
of compliance procedures will be allowed, if
approved by the Wichita Aircraft
This procedure is to be used to detect
cracks in the inner and outer spars of the
front and rear spar assemblies of Raytheon
Aircraft Company Beech Models 45 (YT–34),
A45 (T–34A, B–45), and D45 (T–34B)
airplane stabilizers outside of the steel
bushings in the attach holes.
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Purpose
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Federal Register / Vol. 72, No. 66 / Friday, April 6, 2007 / Rules and Regulations
Area To Be Inspected
To access the area of inspection, remove
the stabilizer from the airplane. The areas to
be inspected include the forward and aft
surfaces of the inner and outer front and rear
spars of the horizontal stabilizers in the areas
surrounding each of the attach holes.
Preparing the Area for Inspection
Thoroughly clean area to be inspected with
solvent (acetone or equivalent) as required
until no signs of dirt, grime, or oil remain on
the front and rear spars from the closeout
former inboard on the forward and aft
surfaces of the spars.
Surfaces to be inspected should be smooth
and corrosion-free. Any loss of thickness due
to corrosion below material thickness
tolerance is cause for rejection of the
structure. An ultrasonic tester may be used
to determine if material thickness has been
compromised.
Equipment Requirements
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Nortec Stavely 2000D Eddy Current Tester
or equivalent.
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Probe: 50–500 KHz, shielded, absolute,
0.071″ diameter (0.090 max. diameter), right
angle, pencil style, surface probe, 5″ long,
drop or equivalent. Use 0.025′ notch (beyond
head) for calibration.
Personal Requirements
Technicians with Eddy Current, Level II or
Level III per one of the following
specifications: ATA specification 105, SNT–
TC–1A, or NAS–410 (MIL-std 410E).
Methods
Typical Set-up Parameters:
Frequency ¥350 KHz, Gain Vertical ¥75
dB, Horizontal ¥69 dB, Drive-Mid, Filters-Lo
Pass-30, Hi Pass-0, Lift off-Horizontal to the
left, adjust as required. The most reliable
indication (minimum of 1⁄2 to 2 graticules) of
the smallest observable flaw in the coupon
(see the attached Figures) occurs from the
notch extending 0.025″ past the edge of the
nominal fastener head (total notch length of
0.100″ from the edge of the nominal hole).
Install appropriate aluminum guide pin into
bushing such that the edge of the guide pin
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is flush with the edge of the bushing. Using
the pin (see the attached Figures) as a guide,
circle the area surrounding the steel bushing
with the probe and adjacent area
(approximately 1⁄4″) to inspect for cracks.
Inspect forward and aft surfaces surrounding
bushings of each spar.
Note: T–34 Spar Corporation, 2800 Airport
Road, Hanger A, Ada, Oklahoma 74820 is a
source for these coupons and pin.
Accept/Reject Criteria
Any repeatable flaw indication is cause for
rejection in accordance with the procedure.
In the event that any crack is detected,
describe the flaw in detail providing sketch
as needed and send the information to the
Wichita ACO.
Documentation Requirements
Record inspection findings in the aircraft
logbook.
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Federal Register / Vol. 72, No. 66 / Friday, April 6, 2007 / Rules and Regulations
16998
Federal Register / Vol. 72, No. 66 / Friday, April 6, 2007 / Rules and Regulations
Issued in Kansas City, Missouri, on March
30, 2007.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 07–1715 Filed 4–5–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27687; Directorate
Identifier 2000–NE–42–AD; Amendment 39–
15012; AD 2007–07–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company CF34–1A, –3A, –3A1,
–3A2, –3B, and –3B1 Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is superseding an
existing airworthiness directive (AD) for
General Electric Company (GE) CF34–
1A, –3A, –3A1, –3A2, –3B, and –3B1
turbofan engines. That AD requires a
onetime inspection of certain fan disks
for electrical arc-out indications,
replacing fan disks with electrical arcout indications, and reducing the life
limit of certain fan disks. This AD
requires the same reduced life limit of
certain fan disks, but requires on-wing
inspection of certain fan disks installed
on regional jets within 500 flight hours
after the effective date of this AD. This
AD also requires more enhanced shoplevel inspections of all fan disks for
electrical arc-out defects. This AD
results from a report that in January
2007, a CF34–3B1 turbofan engine
experienced an uncontained fan disk
failure during flight operation. We are
issuing this AD to prevent an
uncontained fan disk failure and
airplane damage.
DATES: Effective April 23, 2007. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of April 23, 2007.
We must receive any comments on
this AD by June 5, 2007.
ADDRESSES: Use one of the following
addresses to comment on this AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
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SUMMARY:
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and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact General Electric Company via
Lockheed Martin Technology Services,
10525 Chester Road, Suite C, Cincinnati,
Ohio 45215; telephone (513) 672–8400;
fax (513) 672–8422, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tara
Chaidez, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail: tara.chaidez@faa.gov; telephone
(781) 238–7773; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: On
February 24, 2006, the FAA issued AD
2006–05–04, Amendment 39–14501 (71
FR 10832; March 3, 2006). That AD
requires a onetime inspection, and if
necessary replacement of certain fan
disks for electrical arc-out defects. That
AD also reduces the life limit of certain
fan disks. That AD was the result of a
fan disk crack found during a visual
inspection as part of routine engine
maintenance. That condition, if not
corrected, could result in an
uncontained failure of the engine.
Actions Since AD 2006–05–04 was
Issued
Since that AD was issued, a CF34–
3B1 turbofan engine experienced an
uncontained fan disk failure during
flight operation, in January 2007. An
inspection of the recovered segments of
the fan disk found an electrical arc-out
defect at the fracture origin site. The fan
disk was marked using the electrochemical etch marking (ECM) procedure
during engine assembly. If the ECM
procedure is performed incorrectly, an
arc-out defect can occur. This arc-out
defect, caused during part marking,
resulted in the uncontained failure.
The uncontained fan disk failure
during flight operation in January 2007
showed that the inspections in GE
Service Bulletin No. CF34–BJ 72–
A0088, Revision 1, dated October 30,
2000 and in GE Alert Service Bulletin
(ASB) No. CF34–AL 72–A0103, dated
August 4, 2000, mandated by AD 2006–
05–04, are not adequate to find all
electrical arc-out defects.
We issued emergency AD 2007–04–51
on February 16, 2007, and its follow-up
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published version, AD 2007–05–16, on
February 28, 2007, to perform an
enhanced onetime inspection of a highrisk suspect population of 31 fan disks.
While complying with those ADs,
operators found indications of
additional electrical arc-out defects.
Because these additional indications
of electrical arc-out defects validate our
concern for the significant risk posed in
the remaining suspect population of fan
disks, we are issuing this final rule;
request for comments AD. This AD
requires an accelerated inspection
schedule using the improved
inspections of the three GE ASBs listed
below. These ASBs include fluorescent
penetrant inspection (FPI), tactile and
enhanced visual (TEV) inspection, and
eddy current inspection (ECI) for
finding electrical arc-out defects. This
condition, if not corrected, could result
in an uncontained fan disk failure and
airplane damage.
Relevant Service Information
We have reviewed and approved the
technical contents of GE ASBs No.
CF34–BJ S/B 72–A0212, Revision 2,
dated March 22, 2007, ASB No. CF34–
AL S/B 72–A0233, Revision 2, dated
March 22, 2007, and ASB No. CF34–AL
S/B 72–A0231, dated March 7, 2007. All
three ASBs list the affected fan disks by
serial number and part number. The
first two ASBs describe procedures for
performing FPI, a tactile and TEV
inspection, and ECI for cracks and
electrical arc-out defects. The third ASB
describes procedures for performing an
on-wing TEV inspection of fan disks for
electrical arc-out defects.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other GE CF34–1A, –3A, –3A1,
–3A2, –3B, and –3B1 turbofan engines
of the same type design. We are issuing
this AD to prevent an uncontained fan
disk failure and airplane damage. This
AD requires on-wing TEV inspection of
fan disks for electrical arc-out defects on
fan disks installed on regional jets
within 500 flight hours after the
effective date of this AD. This AD also
requires for all affected fan disks shoplevel FPI, enhanced TEV, and ECI
inspections for cracks and electrical arcout defects. This AD also carries
forward from AD 2006–05–04 the
reduced life limit for certain fan disks.
You must use the service information
described previously to perform the
actions required by this AD.
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]]>Agencies
[Federal Register Volume 72, Number 66 (Friday, April 6, 2007)]
[Rules and Regulations]
[Pages 16990-16998]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 07-1715]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25105; Directorate Identifier 2006-CE-33-AD;
Amendment 39-15016; AD 2007-06-01 R1]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Beech Models
45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; correction.
-----------------------------------------------------------------------
SUMMARY: We are clarifying information contained in Airworthiness
Directive (AD) 2007-06-01, which supersedes AD 62-24-01 and applies to
all Raytheon Aircraft Company (RAC) Beech Models 45 (YT-34), A45 (T-
34A, B45), and D45 (T-34B) airplanes. AD 2007-06-01 currently requires
you to repetitively inspect, using the eddy current method, the front
and rear horizontal stabilizer spars for cracks and replace any cracked
stabilizer. We inadvertently left out the language in this AD that
required replacement of any horizontal stabilizer spar found cracked
prior to further flight although the procedures in the appendix made
reference to corrective action. The replacement information was
contained in the notice of proposed rulemaking (NPRM). This document
adds this information already proposed back into the AD. We are issuing
this AD to prevent failure of the front and/or rear horizontal
stabilizer spars caused by fatigue cracks. This failure could result in
stabilizer separation and loss of control of the airplane.
DATES: This AD becomes effective on April 16, 2007.
ADDRESSES: To view the AD docket, go to the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC 20590-001 or on the Internet at
https://dms.dot.gov. The docket number is FAA-2006-25105; Directorate
Identifier 2006-CE-33-AD.
FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent
Airport, Wichita, Kansas 67209; telephone: (316) 946-4155; fax: (316)
946-4107.
SUPPLEMENTARY INFORMATION:
[[Page 16991]]
Discussion
On March 5, 2007, we issued AD 2007-06-01, Amendment 39-14982 (72
FR 10909, March 12, 2007), to supersede AD 62-24-01. AD 2007-06-01
retained inspections of the front and rear horizontal stabilizer spars
for cracks, but changed the inspection method from the dye penetrant
method to the surface eddy current method.
We inadvertently left out the language in AD 2007-06-01 that
required replacement of any horizontal stabilizer spar found cracked
prior to further flight although the procedures in the appendix made
reference to corrective action. The replacement information was
contained in the NPRM.
Consequently, the FAA sees a need to clarify AD 2007-06-01 to
assure that any cracked horizontal stabilizer spar is replaced prior to
further flight.
Correction of Publication
This document clarifies AD 2007-06-01 by incorporating the
replacement language that was proposed in the NPRM and adds the
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR
39.13).
Since this action only clarifies the intent of what was originally
proposed in the NPRM, it has no adverse economic impact and imposes no
additional burden on any person than was already proposed. Therefore,
the FAA has determined that prior notice and opportunity for public
comment are unnecessary.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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)
2007-06-01, Amendment 39-14982 (72 FR 10909, March 12, 2007), and
adding the following new AD:
2007-06-01 R1 Raytheon Aircraft Company: Amendment 39-15016; Docket
No. FAA-2006-25105; Directorate Identifier 2006-CE-33-AD.
Effective Date
(a) This AD becomes effective on April 16, 2007.
Affected ADs
(b) This AD revises AD 2007-06-01, Amendment 39-14982, which
superseded AD 62-24-01, Amendment 39-508.
Applicability
(c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
Beech 45 (YT-34)............................ All.
Beech A45 (T34A, B-45)...................... All.
Beech D45 (T-34B)........................... All.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD is intended to prevent failure of the front and/or
rear horizontal stabilizer spars caused by fatigue cracks by
changing the inspection method from dye penetrant to surface eddy
current. This failure could result in stabilizer separation and loss
of control of the airplane.
Compliance
(e) Using the surface eddy current inspection procedures
outlined in the appendix of this AD, inspect the front and rear
horizontal stabilizer spars between the butt rib and the inboard end
for cracks, unless already done, as presented below. If any crack is
found in either spar or the reinforcing doubler during any
inspection required by this AD, prior to further flight, replace the
stabilizer and continue to repetitively inspect at intervals not to
exceed 500 hours time-in-service (TIS).
(1) If the last inspection of the front and rear horizontal
stabilizer spars was done using the surface eddy current method (or
FAA-approved equivalent method) to show compliance with AD 62-24-01
and/or to show compliance with the alternative method of compliance
(AMOC) to AD 2004-25-51: Repetitively inspect thereafter at
intervals not to exceed 500 hours TIS.
(2) If the last inspection of the front and rear horizontal
stabilizer spars required by AD 62-24-01 was done using the dye
penetrant method: Inspect initially as presented in the table below
and repetitively thereafter at intervals not to exceed 500 hours
TIS:
----------------------------------------------------------------------------------------------------------------
If Then
----------------------------------------------------------------------------------------------------------------
(i) Less than 200 hours TIS have passed since the Inspect at whichever of the following occurs later:
last inspection required by AD 62-24-01: (A) Upon accumulating 200 hours TIS since the last
inspection required by AD 62-24-01; or
(B) Within the next 6 months after April 16, 2007 (the
effective date of this AD).
(ii) 200 hours TIS or more have passed since the Inspect at whichever of the following occurs first, unless
last inspection required by AD 62-24-01: paragraph (e)(2)(iii) of this AD applies, as specified
below:
(A) At the next repetitive inspection required by AD 62-24-
01; or
(B) Within the next 6 months after April 16, 2007 (the
effective date of this AD).
(iii) Paragraph (e)(2)(ii) results in the initial Inspect within the next 30 days after April 16, 2007 (the
surface eddy current inspection becoming mandatory effective date of this AD).
within 30 days after the effective date of this AD:
----------------------------------------------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office, FAA,
ATTN: T.N. Baktha, Aerospace Engineer, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4155;
fax: (316) 946-4107, has the authority to approve AMOCs for this AD,
if requested using the procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 62-24-01 are approved for this AD.
Appendix to AD 2007-06-01 R1--Surface Eddy Current Inspection Procedure
Note: This surface eddy current inspection procedure is based on
T-34 Spar Corporation TSC 3506, Rev C, dated May 10, 2005. The T-34
Spar Corporation is allowing the use of this procedure to be
included in this Airworthiness Directive. Alternative methods of
compliance procedures will be allowed, if approved by the Wichita
Aircraft Certification Office and requested using the procedures
found in 14 CFR 39.19.
Purpose
This procedure is to be used to detect cracks in the inner and
outer spars of the front and rear spar assemblies of Raytheon
Aircraft Company Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45
(T-34B) airplane stabilizers outside of the steel bushings in the
attach holes.
[[Page 16992]]
Area To Be Inspected
To access the area of inspection, remove the stabilizer from the
airplane. The areas to be inspected include the forward and aft
surfaces of the inner and outer front and rear spars of the
horizontal stabilizers in the areas surrounding each of the attach
holes.
Preparing the Area for Inspection
Thoroughly clean area to be inspected with solvent (acetone or
equivalent) as required until no signs of dirt, grime, or oil remain
on the front and rear spars from the closeout former inboard on the
forward and aft surfaces of the spars.
Surfaces to be inspected should be smooth and corrosion-free.
Any loss of thickness due to corrosion below material thickness
tolerance is cause for rejection of the structure. An ultrasonic
tester may be used to determine if material thickness has been
compromised.
Equipment Requirements
Nortec Stavely 2000D Eddy Current Tester or equivalent.
Probe: 50-500 KHz, shielded, absolute, 0.071'' diameter (0.090
max. diameter), right angle, pencil style, surface probe, 5'' long,
drop or equivalent. Use 0.025' notch (beyond head) for calibration.
Personal Requirements
Technicians with Eddy Current, Level II or Level III per one of
the following specifications: ATA specification 105, SNT-TC-1A, or
NAS-410 (MIL-std 410E).
Methods
Typical Set-up Parameters:
Frequency -350 KHz, Gain Vertical -75 dB, Horizontal -69 dB,
Drive-Mid, Filters-Lo Pass-30, Hi Pass-0, Lift off-Horizontal to the
left, adjust as required. The most reliable indication (minimum of
\1/2\ to 2 graticules) of the smallest observable flaw in the coupon
(see the attached Figures) occurs from the notch extending 0.025''
past the edge of the nominal fastener head (total notch length of
0.100'' from the edge of the nominal hole). Install appropriate
aluminum guide pin into bushing such that the edge of the guide pin
is flush with the edge of the bushing. Using the pin (see the
attached Figures) as a guide, circle the area surrounding the steel
bushing with the probe and adjacent area (approximately \1/4\'') to
inspect for cracks. Inspect forward and aft surfaces surrounding
bushings of each spar.
Note: T-34 Spar Corporation, 2800 Airport Road, Hanger A, Ada,
Oklahoma 74820 is a source for these coupons and pin.
Accept/Reject Criteria
Any repeatable flaw indication is cause for rejection in
accordance with the procedure. In the event that any crack is
detected, describe the flaw in detail providing sketch as needed and
send the information to the Wichita ACO.
Documentation Requirements
Record inspection findings in the aircraft logbook.
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Issued in Kansas City, Missouri, on March 30, 2007.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 07-1715 Filed 4-5-07; 8:45 am]
BILLING CODE 4910-13-P
