Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes, 82219-82228 [2010-32905]
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Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Rules and Regulations
82219
PART 228—COMMUNITY
REINVESTMENT (REGULATION BB)
PART 563e—COMMUNITY
REINVESTMENT
1. The authority citation for part 228
continues to read as follows:
■
1. The authority citation for part 563e
continues to read as follows:
14 CFR Part 39
Authority: 12 U.S.C. 321, 325, 1828(c),
1842, 1843, 1844, and 2901 et seq.
Authority: 12 U.S.C. 1462a, 1463, 1464,
1467a, 1814, 1816, 1828(c), and 2901 through
2907.
[Docket No. FAA–2010–0827; Directorate
Identifier 2010–CE–029–AD; Amendment
39–16552; AD 2010–17–18 R1]
2. Revise § 563e.12(u)(1) to read as
follows:
RIN 2120–AA64
■
2. Revise § 228.12(u)(1) to read as
follows:
■
§ 228.12
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
■
Definitions.
*
*
*
*
*
(u) Small bank—(1) Definition. Small
bank means a bank that, as of December
31 of either of the prior two calendar
years, had assets of less than $1.122
billion. Intermediate small bank means
a small bank with assets of at least $280
million as of December 31 of both of the
prior two calendar years and less than
$1.122 billion as of December 31 of
either of the prior two calendar years.
*
*
*
*
*
Federal Deposit Insurance Corporation
12 CFR Chapter III
Authority and Issuance
For the reasons set forth in the joint
preamble, the Board of Directors of the
Federal Deposit Insurance Corporation
amends part 345 of chapter III of title 12
of the Code of Federal Regulations to
read as follows:
■
§ 563e.12
Definitions.
*
*
*
*
*
(u) Small savings association—(1)
Definition. Small savings association
means a savings association that, as of
December 31 of either of the prior two
calendar years, had assets of less than
$1.122 billion. Intermediate small
savings association means a small
savings association with assets of at
least $280 million as of December 31 of
both of the prior two calendar years and
less than $1.122 billion as of December
31 of either of the prior two calendar
years.
*
*
*
*
*
Dated: December 7, 2010.
Julie L. Williams,
First Senior Deputy Comptroller and Chief
Counsel.
PART 345—COMMUNITY
REINVESTMENT
By order of the Board of Governors of the
Federal Reserve System, acting through the
Secretary of the Board under delegated
authority, December 15, 2010.
■
1. The authority citation for part 345
continues to read as follows:
Robert deV. Frierson,
Deputy Secretary of the Board.
Authority: 12 U.S.C. 1814–1817, 1819–
1820, 1828, 1831u and 2901–2907, 3103–
3104, and 3108(a).
By order of the Board of Directors.
Dated at Washington, DC, this 14th day of
December 2010.
Federal Deposit Insurance Corporation.
2. Revise § 345.12(u)(1) to read as
follows:
■
§ 345.12
Definitions.
*
*
*
*
(u) Small bank—(1) Definition. Small
bank means a bank that, as of December
31 of either of the prior two calendar
years, had assets of less than $1.122
billion. Intermediate small bank means
a small bank with assets of at least $280
million as of December 31 of both of the
prior two calendar years and less than
$1.122 billion as of December 31 of
either of the prior two calendar years.
*
*
*
*
*
srobinson on DSKHWCL6B1PROD with RULES
*
Valerie J. Best,
Assistant Executive Secretary.
Dated: December 9, 2010.
By the Office of Thrift Supervision,
John E. Bowman,
Acting Director.
[FR Doc. 2010–32321 Filed 12–29–10; 8:45 am]
BILLING CODE 6714–01–P, 4810–33–P, 6210–01–P,
6720–01–P
Department of the Treasury
Office of Thrift Supervision
12 CFR Chapter V
For the reasons discussed in the joint
preamble, 12 CFR part 563e is amended
as follows:
■
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Airworthiness Directives; Air Tractor,
Inc. Models AT–802 and AT–802A
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are revising an existing
airworthiness directive (AD) for Air
Tractor, Inc. (Air Tractor) Models AT–
802 and AT–802A airplanes. That AD
currently requires you to repetitively
inspect (using the eddy current method)
the two outboard fastener holes in both
of the wing main spar lower caps at the
center splice joint for cracks and repair
or replace any cracked spar, and
changes the safe life for certain serial
(SN) ranges. This AD retains the actions
of AD 2010–17–18 and reduces the
applicability from all serial numbers
beginning with SN–0001 as required by
the previous AD to SN–0001 through
SN–0269. This AD was prompted by our
evaluation of a comment from David
Ligon, Air Tractor, and our
determination that we should reduce
the applicability from that already
required by the previous AD. We are
issuing this AD to detect and correct
cracks in the wing main spar lower cap
at the center splice joint, which could
result in failure of the spar cap and lead
to wing separation and loss of control of
the airplane.
DATES: This AD is effective January 14,
2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 9, 2010 (75 FR 52255,
August 25, 2010).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of April 21, 2006 (71 FR
19994, April 19, 2006).
We must receive any comments on
this AD by February 14, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
SUMMARY:
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Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Rules and Regulations
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Air Tractor, Inc., P.O.
Box 485, Olney, Texas 76374;
telephone: (940) 564–5616; fax: (940)
564–5612; E-mail:
airmail@airtractor.com; Internet: https://
www.airtractor.com. You may review
copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call 816–329–4148.
srobinson on DSKHWCL6B1PROD with RULES
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Andrew McAnaul, Aerospace Engineer,
ASW–150 (c/o MIDO–43), 10100
Reunion Place, Suite 650, San Antonio,
Texas 78216; phone: (210) 308–3365;
fax: (210) 308–3370; e-mail:
andrew.mcanaul@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 11, 2010, we issued AD
2010–17–18, amendment 39–16412 (75
FR 52255, August 25, 2010), for all Air
Tractor Models AT–802 and AT–802A
airplanes. That AD requires you to
repetitively inspect (using the eddy
current method) the two outboard
fastener holes in both of the wing main
spar lower caps at the center splice joint
for cracks and repair or replace any
cracked spar, and changes the safe life
for certain SN ranges. That AD resulted
from the FAA’s evaluation of service
information issued by Air Tractor and
our determination that we needed to
add inspections, add modifications, and
change the safe life for certain SN
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ranges. We issued that AD to detect and
correct cracks in the wing main spar
lower cap at the center splice joint,
which could result in failure of the spar
cap and lead to wing separation and loss
of control of the airplane.
Actions Since AD was Issued
Since we issued AD 2010–17–18, we
have evaluated a comment from David
Ligon, Air Tractor, and determined that
we should reduce the applicability from
all serial numbers beginning with SN–
0001 as required by the previous AD to
SN–0001 through SN–0269. Airplane
SN–0270 and subsequent wing main
spar components are life limited at
11,700 hours time-in-service as
described in Air Tractor, Inc. AT 802/
802A Airworthiness Limitations, Pages
6–i, 6–1, and 6–2, dated: September 16,
2009.
Relevant Service Information
We reviewed the following service
information from Snow Engineering Co.:
• Service Letter #80GG, revised
December 21, 2005;
• Service Letter #284, dated October
4, 2009;
• Service Letter #281, dated August 1,
2009;
• Service Letter #245, dated April 25,
2005;
• Service Letter #240, dated
September 30, 2004;
• Process Specification #197, page 1,
revised June 4, 2002; pages 2 through 4,
dated February 23, 2001; and page 5,
dated May 3, 2002;
• Drawing Number 20995, Sheet 3,
dated November 25, 2005;
• Drawing Number 20995, Sheet 2,
Rev. D., dated November 25, 2005; and
• Drawing Number 20975, Sheet 4,
Rev. A., dated January 7, 2009.
The service information describes
procedures for the following actions:
• Inspection (repetitively) of the two
outboard fastener holes in both of the
wing main spar lower caps at the center
splice joint for cracks;
• Repair or replacement of any
cracked spar cap; and
• Modification option to extend the
safe life limit.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
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AD Requirements
This AD requires accomplishing the
actions specified in the service
information described previously. The
AD also requires sending the inspection
results (if cracks are found) to Andrew
McAnaul, Aerospace Engineer, ASW–
150 (c/o MIDO–43), 10100 Reunion
Place, Suite 650, San Antonio, Texas
78216; phone: (210) 308–3365; fax: (210)
308–3370.
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because the public has already had
the opportunity to comment on the
actions of this unsafe condition. This
action only reduces the applicability
from that already required by the
previous AD. Therefore, we find that
notice and opportunity for prior public
comment are unnecessary and that good
cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2010–0827 and directorate
identifier 2010–CE–029–AD at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD affects 121
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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82221
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Eddy current inspection ......
Spar cap replacement (two
spars).
$500 to $800 .......................
495 work-hours × $85 per
hour = $42,075.
Not Applicable .....................
$39,100 (two spars) ............
$500 to $800 ..................
$81,175 ..........................
We estimate the following costs to do
any necessary center splice plate
installation that would be required
based on the results of the inspection.
We have no way of determining the
Cost on U.S. operators
$60,500 to $96,800
$9,822,175
number of aircraft that might need this
center splice plate installation:
ON-CONDITION COSTS
Action
Labor cost
Center splice plate installation ...................
185 work-hours × $85 per hour = $15,725 ............................................
We estimate the following costs to do
any necessary extended splice block
installation that would be required
Parts cost
based on the results of the inspection.
We have no way of determining the
$4,300
Cost per
product
$20,025
number of aircraft that might need this
extended splice block installation:
ON-CONDITION COSTS
Cost per
product
Action
Labor cost
Parts cost
Extended splice block installation ...................................................................
70 workhours × $85
per hour =
$5,950
$3,200 ................................................
We estimate the following costs to do
any necessary cold-work lower spar cap
fastener holes that would be required
based on the results of the inspection.
We have no way of determining the
$9,150
number of aircraft that might need this
cold-work lower spar cap fastener holes:
ON-CONDITION COSTS
Labor cost
Cold-work lower spar cap fastener holes ...
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Action
$1,350 .....................................................................................................
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
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that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
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.
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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
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Parts cost
Cost per
product
Not
Applicable
$1,350
(3) Will not affect intrastate aviation
in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as
follows:
■
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Applicability
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2010–17–18, amendment 39–16412 (75
FR 52255, August 25, 2010) and adding
the following new AD:
■
2010–17–18 R1 Air Tractor, Inc.:
Amendment 39–16552; Docket No.
FAA–2010–0827; Directorate Identifier
2010–CE–029–AD.
Effective Date
(a) This AD is effective January 14, 2011.
Affected ADs
(b) This AD revises AD 2010–17–18,
Amendment 39–16412.
Unsafe Condition
(c) This AD affects Air Tractor, Inc. Models
AT–802 and AT–802A airplanes, serial
numbers (SNs) –0001 through –0269, that
are:
(1) certificated in any category;
(2) engaged in agricultural dispersal
operations, including those airplanes that
have been converted from fire fighting to
agricultural dispersal or airplanes that
convert between fire fighting and agricultural
dispersal;
(3) not equipped with the factory-supplied
computerized fire gate (part number (P/N)
80540); and
(4) not engaged in only full-time fire
fighting.
(e) This AD was prompted by our
evaluation of a comment from David Ligon,
Air Tractor, and our determination that we
should reduce the applicability from the all
serial numbers beginning with SN –0001 as
required by the previous AD to SN –0001
through SN–0269. We are issuing this AD to
detect and correct cracks in the wing main
spar lower cap at the center splice joint,
which could result in failure of the spar cap
and lead to wing separation and loss of
control of the airplane.
Subject
(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 57: Wings.
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
(g) To address this problem for Models
AT–802 and AT–802A airplanes, SNs –0001
through –0091, you must do the following,
unless already done:
TABLE 1—ACTIONS, COMPLIANCE, AND PROCEDURES
Actions
Compliance
Procedures
(1) Eddy current inspect for cracks the center
splice joint outboard two fastener holes in
both the left and right wing main spar lower
caps.
Initially inspect upon accumulating 1,700
hours time-in-service (TIS) or within the
next 50 hours TIS after April 21, 2006 (the
effective date of AD 2006–08–09), whichever occurs later, and repetitively thereafter
at intervals not to exceed 800 hours TIS. If,
before September 9, 2010 (the effective
date of AD 2010-17-18), you installed the
center splice plate and extended 8-bolt
splice blocks, use the inspection compliance times found in paragraph (g)(5) of this
AD.
Before further flight after the inspection where
a crack was found. If, before the airplane
reaches a total of 3,200 hours TIS, you repair your airplane following paragraph
(g)(2)(i) of this AD, you must do the eddy
current inspections following the compliance
times found in paragraph (g)(5) of this AD.
If, at 3,200 hours TIS or after, you repair
your airplane following paragraph (g)(2)(i) of
this AD, this repair terminates the inspection requirements of paragraph (g)(1) of this
AD.
Follow Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002;
pages 2 through 4, dated February 23,
2001; and page 5, dated May 3, 2002.
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(2) If you find any cracks as a result of any inspection required in paragraph (g)(1) of this
AD, do the following actions:
(i) For cracks that can be repaired, repair the
airplane by doing the following actions:.
(A) Install center splice plate, P/N 20997–2,
and extended 8-bolt splice blocks, P/N
20985–1 & –2, and cold-work the lower spar
cap fastener holes; and.
(B) Eddy current inspect for cracks the center
splice joint outboard two fastener holes in
both the left and right wing main spar lower
caps. This eddy current inspection is required
as part of the modification and is separate
from the inspections required in paragraph
(g)(1) of this AD.
(ii) For cracks that cannot be repaired by incorporating the modification specified above, do
the actions to replace the lower spar caps
and associated parts listed following the procedures identified in paragraph (g)(3) of this
AD.
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Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering Co. Process Specification #197,
page 1, revised June 4, 2002; pages 2
through 4, dated February 23, 2001; and
page 5, dated May 3, 2002; Snow Engineering Co. Drawing Number 20995, Sheet
2, Rev. D., dated November 25, 2005; and
Snow Engineering Co. Service Letter #240,
dated September 30, 2004.
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82223
TABLE 1—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued
Actions
Compliance
Procedures
(3) Replace the wing main spar lower caps, the
web plates, the center joint splice blocks and
hardware, and the wing attach angles and
hardware, and install the steel web splice
plate. This replacement terminates the repetitive inspections required in paragraph (g)(1)
of this AD.
(i) Do the replacement at whichever of the following compliance times occurs first:
(A) Before further flight when cracks are
found that cannot be repaired by incorporating the modification in paragraph
(g)(2)(i) of this AD; or
(B) Before or when the airplane reaches the
wing main spar lower cap safe life of a total
of 4,100 hours TIS or within the next 50
hours TIS after September 9, 2010 (the effective date of AD 2010-17-18), whichever
occurs later.
(ii) After this replacement the new spar safe
life is 11,700 hours TIS. If, before September 9, 2010 (the effective date of AD
2010-17-18), an airplane main spar lower
cap was replaced with P/N 21083–1/–2, the
spar safe life for that P/N spar cap is 8,000
hours TIS until the main spar lower cap is
replaced with P/N 21118–1/–2. The new
spar safe life for P/N 21118–1/–2 is 11,700
hours.
(iii) To extend the initial 4,100 hours TIS safe
life of the wing main spar lower cap to a
total of 8,000 hours TIS, you may incorporate the optional modification specified in
paragraph (g)(4) of this AD.
Modify at whichever of the following compliance times occurs first:
(A) Before further flight after any inspection
required in paragraph (g)(1) of this AD
where a crack is found. If you modify your
airplane before the airplane reaches a total
of 3,200 hours TIS to repair cracks as required in paragraph (g)(2)(i) of this AD, you
must do the eddy current inspections following the compliance times found in paragraph (g)(5) of this AD.
(B) Between 3,200 hours TIS and 4,100 hours
TIS.
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised
December 21, 2005; Snow Engineering Co.
Drawing Number 20975, Sheet 4, Rev. A,
dated January 7, 2009.
(4) To extend the safe life of the wing main
spar lower cap to a total of 8,000 hours TIS,
you may incorporate the following optional
modification. This modification terminates the
repetitive inspections required in paragraph
(g)(1) of this AD, unless you performed the
modification before the airplane reaches a
total of 3,200 hours TIS to repair cracks:
(i) Install center splice plate, P/N 20997–2, and
extended 8-bolt splice blocks, P/N 20985–1 &
–2, and cold-work the lower spar cap fastener holes; and
(ii) Eddy current inspect for cracks the center
splice joint outboard two fastener holes in
both the left and right wing main spar lower
caps. This eddy current inspection is required
as part of the modification and is separate
from the inspections required in paragraph
(g)(1) of this AD.
(5) If, before September 9, 2010 (the
effective date of AD 2010–17–18) or as a
result of performing the repair for cracks
following paragraph (g)(2) of this AD, you
installed the center splice plate and extended
8-bolt splice blocks, use the following table
for compliance times to do the eddy current
inspections required in paragraph (g)(1) of
this AD. If you find any cracks as a result of
any inspection following the compliance
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering Co. Process Specification #197,
page 1, revised June 4, 2002; pages 2
through 4, dated February 23, 2001; and
page 5, dated May 3, 2002; Snow Engineering Co. Drawing Number 20995, Sheet
2, Rev. D., dated November 25, 2005; and
Snow Engineering Co. Service Letter #240,
dated September 30, 2004.
times in the following table, you must do the
replacement action in paragraph (g)(2)(ii) of
this AD:
TABLE 2—EDDY CURRENT INSPECTION COMPLIANCE TIMES
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Condition of the airplane
Initially inspect
Repetitively inspect thereafter at intervals not
to exceed
(i) If the airplane has already had the center
splice plate and extended 8-bolt splice blocks
installed at or after 3,200 hours TIS but the
fastener holes have not been cold worked, at
any time you may cold work the fastener
holes to terminate the repetitive inspection
requirements of this paragraph.
(ii) Before reaching 3,200 hours TIS, the airplane had the center splice plate and extended 8-bolt splice blocks already installed
but the fastener holes have not been cold
worked.
When the airplane reaches a total of 2,400
hours TIS after the modification or within
the next 100 days after September 9, 2010
(the effective date of AD 2010-17-18),
whichever occurs later.
1,200 hours TIS until the 8,000 hours TIS
spar replacement time.
When the airplane reaches a total of 2,400
hours TIS after the modification or within
the next 100 days after September 9, 2010
(the effective date of AD 2010-17-18),
whichever occurs later.
1,200 hours TIS. Upon reaching 4,800 hours
TIS after the modification, inspect repetitively thereafter at intervals not to exceed
600 hours TIS until the 8,000 hours TIS
spar replacement time.
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Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Rules and Regulations
TABLE 2—EDDY CURRENT INSPECTION COMPLIANCE TIMES—Continued
Condition of the airplane
Initially inspect
Repetitively inspect thereafter at intervals not
to exceed
(iii) Before reaching 3,200 hours TIS, the airplane had the center splice plate and extended 8-bolt splice blocks installed and the
fastener holes have been cold worked.
When the airplane reaches a total of 4,800
hours TIS after the modification or within
the next 100 days after September 9, 2010
(the effective date of AD 2010-17-18),
whichever occurs later.
600 hours TIS until the 8,000 hours TIS spar
replacement time.
(h) To address this problem for AT–802
and AT–802A airplanes, SNs–0092 through
–0101, you must do the following, unless
already done:
TABLE 3—ACTIONS, COMPLIANCE, AND PROCEDURES
Actions
Compliance
Procedures
(1) Eddy current inspect for cracks the center
splice joint outboard two fastener holes in
both the left and right wing main spar lower
caps.
Initially inspect upon accumulating 1,700
hours TIS or within the next 50 hours TIS
after September 9, 2010 (the effective date
of AD 2010–17–18), whichever occurs later,
and repetitively thereafter at intervals not to
exceed 800 hours TIS. If the center splice
plate, P/N 20994–2, is installed as specified
in paragraph (h)(4) of this AD, do the repetitive inspections at intervals not to exceed
2,000 hours TIS.
Before further flight after the inspection where
a crack was found. This repair modification
in paragraph (h)(2)(i) of this AD extends the
safe life of the wing main spar lower cap to
a total of 8,000 hours TIS.
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; and Snow
Engineering Co. Process Specification
#197, page 1, revised June 4, 2002; pages
2 through 4, dated February 23, 2001; and
page 5, dated May 3, 2002.
(i) Do the replacement at whichever of the following compliance times occurs first:
(A) Before further flight when cracks are
found that cannot be repaired by incorporating the modification in paragraph
(h)(2)(i) of this AD; or
(B) Before or when the airplane reaches the
wing main spar lower cap safe life of a total
of 4,100 hours TIS or within the next 50
hours TIS after September 9, 2010 (the effective date of AD 2010–17–18), whichever
occurs later.
(ii) To extend the initial 4,100 hours TIS safe
life of the wing main spar lower cap to a
total of 8,000 hours TIS, you may incorporate the optional modification specified in
paragraph (h)(4) of this AD.
(iii)After replacement of the old spar with the
new lower spar cap, P/N 21118–1/–2, the
new spar safe life is 11,700 hours TIS.
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised
December 21, 2005; Snow Engineering Co.
Drawing Number 20975, Sheet 4, Rev. A,
dated January 7, 2009.
srobinson on DSKHWCL6B1PROD with RULES
(2) If you find any cracks as a result of any inspection required by paragraph (h)(1) of this
AD, do the following actions. This repair
modification terminates the repetitive inspections required in paragraph (h)(1) of this AD:
(i) For cracks that can be repaired, repair the
airplane by doing the following actions:
(A) Install the 9-bolt splice blocks and cold-work
the lower spar cap fastener holes;
(B) Eddy current inspect for cracks the center
splice joint outboard two fastener holes in
both the left and right wing main spar lower
caps. This eddy current inspection is required
as part of the repair and is separate from the
inspections required in paragraph (h)(1) of
this AD; and
(C) Install the center splice plate, P/N 20994–2,
per paragraph (h)(4) if not already installed.
(ii) For cracks that cannot be repaired by doing
the actions in paragraph (h)(2)(i) of this AD,
replace the lower spar caps and associated
parts listed following the procedures identified
in paragraph (h)(3) of this AD.
(3) Replace the wing main spar lower caps, the
web plates, the center joint splice blocks and
hardware, and the wing attach angles and
hardware, and install the steel web splice
plate. This replacement terminates the repetitive inspections required in paragraph (h)(1)
of this AD.
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Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; and Snow
Engineering Co. Process Specification
#197, page 1, revised June 4, 2002; pages
2 through 4, dated February 23, 2001; and
page 5, dated May 3, 2002, Snow Engineering Co. Service Letter #281, dated August 1, 2009; and Snow Engineering Co.
Drawing Number 20995, Sheet 3, dated
November 25, 2005.
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Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Rules and Regulations
82225
TABLE 3—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued
Actions
Compliance
Procedures
(4) To extend the safe life of the wing main
spar lower cap to a total of 8,000 hours TIS,
you may incorporate the following optional
modification:
(i) Install center splice plate, P/N 20994–2, if
not already installed as part of a repair, and
cold-work the lower spar cap fastener holes;
and
(ii) Eddy current inspect for cracks the center
splice joint outboard two fastener holes in
both the left and right wing main spar lower
caps. This eddy current inspection is required
as part of the modification and is separate
from the inspections required in paragraph
(h)(1) of this AD.
(5) If you find any cracks as a result of any repetitive inspection required by paragraph
(h)(4) of this AD, do the following actions.
This repair modification terminates the repetitive inspections required in paragraph (h)(4)
of this AD:
(i) For cracks that can be repaired, repair the
airplane by doing the following actions:
(A) Install the 9-bolt splice blocks and cold-work
the lower spar cap fastener holes; and
(B) Eddy current inspect for cracks the center
splice joint outboard two fastener holes in
both the left and right wing main spar lower
caps. This eddy current inspection is required
as part of the repair and is separate from the
inspections required in paragraph (h)(1) of
this AD.
(ii) For cracks that cannot be repaired by doing
the actions in paragraph (h)(5)(i) of this AD,
replace the lower spar caps and associated
parts listed following the procedures identified
in paragraph (h)(3) of this AD.
Before the airplane reaches a total of 4,100
hours TIS. After installation of the center
splice plate, P/N 20994–2, do the repetitive
inspections required in paragraph (h)(1) at
intervals not to exceed 2,000 hours TIS. If
as of September 9, 2010 (the effective date
of AD 2010–17–18) you have already exceeded the 4,100 hours TIS threshold for
extending the safe life to 8,000 hours TIS,
you may be eligible for an alternative method of compliance following paragraph (n) in
this AD.
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering Co. Process Specification #197,
page 1, revised June 4, 2002; pages 2
through 4, dated February 23, 2001; and
page 5, dated May 3, 2002; Snow Engineering Co. Drawing Number 20975, Sheet
4, Rev. A., dated January 7, 2009; and
Snow Engineering Co. Service Letter #245,
dated April 25, 2005.
Before further flight after the inspection where
a crack was found.
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; and Snow
Engineering Co. Process Specification
#197, page 1, revised June 4, 2002; pages
2 through 4, dated February 23, 2001; and
page 5, dated May 3, 2002, Snow Engineering Co. Service Letter #281, dated August 1, 2009; and Snow Engineering Co.
Drawing Number 20995, Sheet 3, dated
November 25, 2005.
(i) To address this problem for AT–802 and
AT–802A airplanes, SNs –0102 through
–0178, you must do the following, unless
already done:
TABLE 4—ACTIONS, COMPLIANCE, AND PROCEDURES
Compliance
Procedures
(1) Do an initial eddy current inspection for
cracks of the center splice joint outboard two
fastener holes in both the left and right wing
main spar lower caps. After this initial inspection, you may do the optional cold-working of
the lower spar cap fastener holes to increase
the hours TIS between repetitive inspections
required in paragraph (i)(2) of this AD.
(2) Repetitively eddy current inspect for cracks
the center splice joint outboard two fastener
holes in both the left and right wing main
spar lower caps.
srobinson on DSKHWCL6B1PROD with RULES
Actions
Before the airplane reaches a total of 5,500
hours TIS or within the next 50 hours TIS
after September 9, 2010 (the effective date
of AD 2010-17-18), whichever occurs later.
Follow Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002;
pages 2 through 4, dated February 23,
2001; and page 5, dated May 3, 2002;
Snow Engineering Co. Service Letter #245,
dated April 25, 2005; and Snow Engineering Co. Service Letter #284, dated October
4, 2009.
Follow Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002;
pages 2 through 4, dated February 23,
2001; and page 5, dated May 3, 2002;
Snow Engineering Co. Service Letter #284,
dated October 4, 2009; and (optional) Snow
Engineering Co. Service Letter #245, dated
April 25, 2005.
VerDate Mar<15>2010
17:29 Dec 29, 2010
Jkt 223001
(i) For fastener holes that are cold-worked:
After the initial inspection, repetitively thereafter inspect at intervals not to exceed
2,200 hours TIS.
(ii) For fastener holes not cold-worked: After
the initial inspection, repetitively thereafter
inspect at intervals not to exceed 1,100
hours TIS.
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Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Rules and Regulations
TABLE 4—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued
Actions
Compliance
Procedures
(3) If you find any cracks as a result of any inspection required by paragraphs (i)(1) and
(i)(2) of this AD, do the following actions.
This modification terminates the repetitive inspections required in paragraph (i)(1) and
(i)(2) of this AD:
(i) For cracks that can be repaired, repair the
airplane by doing the following actions:
(A) Install the 9-bolt splice blocks and cold-work
the lower spar cap fastener holes; and
(B) Eddy current inspect for cracks the center
splice joint outboard two fastener holes in
both the left and right wing main spar lower
caps. This eddy current inspection is required
as part of the repair and is separate from the
inspections required in paragraphs (i)(1) and
(i)(2) of this AD.
(ii) For cracks that cannot be repaired by doing
the actions in paragraph (i)(3)(i) of this AD,
replace the lower spar caps and associated
parts listed following the procedures in paragraph (i)(4) of this AD.
(4) Replace the wing main spar lower caps, the
web plates, the center joint splice blocks and
hardware, and the wing attach angles and
hardware, and install the steel web splice
plate. This replacement terminates the repetitive inspections required in paragraphs (i)(1)
and (i)(2) of this AD.
Before further flight after the inspection where
a crack was found.
Follow Snow Engineering Co. Service Letter
#281, dated August 1, 2009; and Snow Engineering Co. Drawing Number 20995,
Sheet 3, dated November 25, 2005.
(i) Do the replacement at whichever of the following compliance times occurs first:
(A) Before further flight when cracks are
found that cannot be repaired by incorporating the repair in paragraph (i)(3)(i) of
this AD; or
(B) Before or when the airplane reaches the
wing main spar lower cap safe life of a total
of 8,000 hours TIS or within the next 50
hours TIS after September 9, 2010 (the effective date of AD 2010-17-18), whichever
occurs later.
(ii) After this replacement the new spar safe
life is 11,700 hours TIS.
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised
December 21, 2005; Snow Engineering Co.
Drawing Number 20975, Sheet 4, Rev. A,
dated January 7, 2009.
(j) To address this problem for AT–802 and
AT–802A airplanes, SNs –0179 through
–0269, you must do the following, unless
already done:
TABLE 5—ACTIONS, COMPLIANCE, AND PROCEDURES
Compliance
Procedures
Replace the wing main spar lower caps, the
web plates, the center joint splice blocks and
hardware, and the wing attach angles and
hardware, and install the steel web splice
plate.
srobinson on DSKHWCL6B1PROD with RULES
Actions
By the 8,000 hours TIS safe-life or within the
next 50 hours TIS after September 9, 2010
(the effective date of AD 2010-17-18),
whichever occurs later. After this replacement the subsequent new spar safe life is
11,700 hours TIS.
Follow Snow Engineering Co. Service Letter
#284, dated October 4, 2009; Snow Engineering Co. Service Letter #80GG, revised
December 21, 2005; Snow Engineering Co.
Drawing Number 20975, Sheet 4, Rev. A,
dated January 7, 2009.
(k) Report any crack from any inspection
required in paragraphs (g), (h), or (i) of this
AD within 10 days after the cracks are found
on the form in Figure 1 of this AD.
(1) Send your report to Andrew McAnaul,
Aerospace Engineer, ASW–150 (c/o MIDO–
43), 10100 Reunion Place, Suite 650, San
Antonio, Texas 78216; phone: (210) 308–
3365; fax: (210) 308–3370.
(2) The Office of Management and Budget
(OMB) approved the information collection
VerDate Mar<15>2010
17:29 Dec 29, 2010
Jkt 223001
requirements contained in this regulation
under the provisions of the Paperwork
Reduction Act and assigned OMB Control
Number 2120–0056.
Special Permit Flight
(l) Under 14 CFR 39.23, we are allowing
special flight permits for the purpose of
compliance with this AD under the following
conditions:
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(1) Only operate in day visual flight rules
(VFR).
(2) Ensure that the hopper is empty.
(3) Limit airspeed to 135 miles per hour
(mph) indicated airspeed (IAS).
(4) Avoid any unnecessary g-forces.
(5) Avoid areas of turbulence.
(6) Plan the flight to follow the most direct
route.
BILLING CODE 4910–13–P
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BILLING CODE 4910–13–C
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Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Rules and Regulations
82228
Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Rules and Regulations
Paperwork Reduction Act Burden Statement
(m) A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, Fort Worth Airplane
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your Principal Maintenance Inspector
or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(3) AMOCs approved for AD 2010–17–18
are approved as AMOCs for this AD.
Related Information
(o) For more information about this AD,
contact Andrew McAnaul, Aerospace
Engineer, ASW–150 (c/o MIDO–43), 10100
Reunion Place, Suite 650, San Antonio,
Texas 78216; phone: (210) 308–3365; fax:
(210) 308–3370; e-mail:
andrew.mcanaul@faa.gov.
Material Incorporated by Reference
(p)(1) You must use the service information
contained in table 6 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register previously approved the
incorporation by reference of the service
information contained in table 6 of this AD
on the date specified in the column
‘‘Incorporation by Reference Approval Date’’
of Table 6.
TABLE 6—MATERIAL INCORPORATED BY REFERENCE
Revision
Date
Incorporation by reference approval date
(i) Snow Engineering Co. Service Letter
#80GG.
(ii) Snow Engineering Co. Service Letter #284
Not Applicable ............
December 21, 2005 ...
Not Applicable ............
October 4, 2009 .........
(iii) Snow Engineering Co. Service Letter #281
Not Applicable ............
August 1, 2009 ...........
(iv) Snow Engineering Co. Service Letter #245
Not Applicable ............
April 25, 2005 .............
(v) Snow Engineering Co. Service Letter #240
(vi) Snow Engineering Co. Process Specification #197:
page 1 .......................................................
pages 2 through 4 .....................................
page 5 .......................................................
(vii) Snow Engineering Co. Drawing Number
20995:
Sheet 2 ......................................................
Not Applicable ............
.....................................
September 30, 2004 ..
.....................................
September 9, 2010 (75 FR 52255, August
25, 2010).
September 9, 2010 (75 FR 52255, August
25, 2010).
September 9, 2010 (75 FR 52255, August
25, 2010).
September 9, 2010 (75 FR 52255, August
25, 2010).
April 21, 2006 (71 FR 19994, April 19, 2006).
April 21, 2006 (71 FR 19994, April 19, 2006).
Not Applicable ............
Not Applicable ............
Not Applicable ............
.....................................
June 4, 2002 ..............
February 23, 2001 ......
May 3, 2002 ...............
.....................................
Rev. D ........................
November 25, 2005 ...
Sheet 3 ......................................................
Not Applicable ............
November 25, 2005 ...
(viii) Snow Engineering Co. Drawing Number
20975, Sheet 4.
srobinson on DSKHWCL6B1PROD with RULES
Document
Rev. A ........................
January 7, 2009 .........
(2) For service information identified in
this AD, contact Air Tractor, Inc., P.O. Box
485, Olney, Texas 76374; telephone: (940)
564–5616; fax: (940) 564–5612; E-mail:
airmail@airtractor.com; Internet:
www.airtractor.com.
(3) You may review copies of the service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
816–329–4148.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Kansas City, Missouri, on
December 16, 2010.
William J. Timberlake,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
VerDate Mar<15>2010
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Jkt 223001
[FR Doc. 2010–32905 Filed 12–29–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 95
[Docket No. 30760; Amdt. No. 491]
IFR Altitudes; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
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April 21, 2006 (71 FR 19994, April 19, 2006).
April 21, 2006 (71 FR 19994, April 19, 2006).
April 21, 2006 (71 FR 19994, April 19, 2006).
September 9, 2010 (75 FR 52255, August
25, 2010).
September 9, 2010 (75 FR 52255, August
25, 2010).
September 9, 2010 (75 FR 52255, August
25, 2010).
September 9, 2010 (75 FR 52255, August
25, 2010).
ACTION:
Final rule.
This amendment adopts
miscellaneous amendments to the
required IFR (instrument flight rules)
altitudes and changeover points for
certain Federal airways, jet routes, or
direct routes for which a minimum or
maximum en route authorized IFR
altitude is prescribed. This regulatory
action is needed because of changes
occurring in the National Airspace
System. These changes are designed to
provide for the safe and efficient use of
the navigable airspace under instrument
conditions in the affected areas.
DATES: Effective Date: 0901 UTC,
January 13, 2011.
FOR FURTHER INFORMATION CONTACT:
Harry Hodges, Flight Procedure
Standards Branch (AMCAFS–420),
SUMMARY:
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]]>Agencies
[Federal Register Volume 75, Number 250 (Thursday, December 30, 2010)]
[Rules and Regulations]
[Pages 82219-82228]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32905]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0827; Directorate Identifier 2010-CE-029-AD;
Amendment 39-16552; AD 2010-17-18 R1]
RIN 2120-AA64
Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-
802A Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are revising an existing airworthiness directive (AD) for
Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes.
That AD currently requires you to repetitively inspect (using the eddy
current method) the two outboard fastener holes in both of the wing
main spar lower caps at the center splice joint for cracks and repair
or replace any cracked spar, and changes the safe life for certain
serial (SN) ranges. This AD retains the actions of AD 2010-17-18 and
reduces the applicability from all serial numbers beginning with SN-
0001 as required by the previous AD to SN-0001 through SN-0269. This AD
was prompted by our evaluation of a comment from David Ligon, Air
Tractor, and our determination that we should reduce the applicability
from that already required by the previous AD. We are issuing this AD
to detect and correct cracks in the wing main spar lower cap at the
center splice joint, which could result in failure of the spar cap and
lead to wing separation and loss of control of the airplane.
DATES: This AD is effective January 14, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 9,
2010 (75 FR 52255, August 25, 2010).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of April
21, 2006 (71 FR 19994, April 19, 2006).
We must receive any comments on this AD by February 14, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-
[[Page 82220]]
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue,
SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Air Tractor,
Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564-5616; fax:
(940) 564-5612; E-mail: airmail@airtractor.com; Internet: https://www.airtractor.com. You may review copies of the referenced service
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas
City, Missouri 64106. For information on the availability of this
material at the FAA, call 816-329-4148.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer,
ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio,
Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; e-mail:
andrew.mcanaul@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 11, 2010, we issued AD 2010-17-18, amendment 39-16412 (75
FR 52255, August 25, 2010), for all Air Tractor Models AT-802 and AT-
802A airplanes. That AD requires you to repetitively inspect (using the
eddy current method) the two outboard fastener holes in both of the
wing main spar lower caps at the center splice joint for cracks and
repair or replace any cracked spar, and changes the safe life for
certain SN ranges. That AD resulted from the FAA's evaluation of
service information issued by Air Tractor and our determination that we
needed to add inspections, add modifications, and change the safe life
for certain SN ranges. We issued that AD to detect and correct cracks
in the wing main spar lower cap at the center splice joint, which could
result in failure of the spar cap and lead to wing separation and loss
of control of the airplane.
Actions Since AD was Issued
Since we issued AD 2010-17-18, we have evaluated a comment from
David Ligon, Air Tractor, and determined that we should reduce the
applicability from all serial numbers beginning with SN-0001 as
required by the previous AD to SN-0001 through SN-0269. Airplane SN-
0270 and subsequent wing main spar components are life limited at
11,700 hours time-in-service as described in Air Tractor, Inc. AT 802/
802A Airworthiness Limitations, Pages 6-i, 6-1, and 6-2, dated:
September 16, 2009.
Relevant Service Information
We reviewed the following service information from Snow Engineering
Co.:
Service Letter 80GG, revised December 21, 2005;
Service Letter 284, dated October 4, 2009;
Service Letter 281, dated August 1, 2009;
Service Letter 245, dated April 25, 2005;
Service Letter 240, dated September 30, 2004;
Process Specification 197, page 1, revised June
4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated
May 3, 2002;
Drawing Number 20995, Sheet 3, dated November 25, 2005;
Drawing Number 20995, Sheet 2, Rev. D., dated November 25,
2005; and
Drawing Number 20975, Sheet 4, Rev. A., dated January 7,
2009.
The service information describes procedures for the following
actions:
Inspection (repetitively) of the two outboard fastener
holes in both of the wing main spar lower caps at the center splice
joint for cracks;
Repair or replacement of any cracked spar cap; and
Modification option to extend the safe life limit.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in the service
information described previously. The AD also requires sending the
inspection results (if cracks are found) to Andrew McAnaul, Aerospace
Engineer, ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San
Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because the
public has already had the opportunity to comment on the actions of
this unsafe condition. This action only reduces the applicability from
that already required by the previous AD. Therefore, we find that
notice and opportunity for prior public comment are unnecessary and
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2010-0827 and directorate identifier 2010-CE-029-
AD at the beginning of your comments. We specifically invite comments
on the overall regulatory, economic, environmental, and energy aspects
of this AD. We will consider all comments received by the closing date
and may amend this AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 121 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 82221]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Eddy current inspection........... $500 to $800........ Not Applicable...... $500 to $800....................... $60,500 to $96,800
Spar cap replacement (two spars).. 495 work-hours x $85 $39,100 (two spars). $81,175............................ $9,822,175
per hour = $42,075.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary center splice
plate installation that would be required based on the results of the
inspection. We have no way of determining the number of aircraft that
might need this center splice plate installation:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Center splice plate installation.............. 185 work-hours x $85 per hour = $4,300 $20,025
$15,725.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary extended
splice block installation that would be required based on the results
of the inspection. We have no way of determining the number of aircraft
that might need this extended splice block installation:
On-Condition Costs
------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
------------------------------------------------------------------------
Extended splice block 70 work- $3,200......... $9,150
installation. hours x $85
per hour =
$5,950
------------------------------------------------------------------------
We estimate the following costs to do any necessary cold-work
lower spar cap fastener holes that would be required based on the
results of the inspection. We have no way of determining the number of
aircraft that might need this cold-work lower spar cap fastener holes:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Cold-work lower spar cap fastener holes....... $1,350................................ Not $1,350
Applicable
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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.
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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
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 FAA amends part 39 of the Federal Aviation Regulations (14 CFR part
39) as follows:
[[Page 82222]]
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)
2010-17-18, amendment 39-16412 (75 FR 52255, August 25, 2010) and
adding the following new AD:
2010-17-18 R1 Air Tractor, Inc.: Amendment 39-16552; Docket No. FAA-
2010-0827; Directorate Identifier 2010-CE-029-AD.
Effective Date
(a) This AD is effective January 14, 2011.
Affected ADs
(b) This AD revises AD 2010-17-18, Amendment 39-16412.
Applicability
(c) This AD affects Air Tractor, Inc. Models AT-802 and AT-802A
airplanes, serial numbers (SNs) -0001 through -0269, that are:
(1) certificated in any category;
(2) engaged in agricultural dispersal operations, including
those airplanes that have been converted from fire fighting to
agricultural dispersal or airplanes that convert between fire
fighting and agricultural dispersal;
(3) not equipped with the factory-supplied computerized fire
gate (part number (P/N) 80540); and
(4) not engaged in only full-time fire fighting.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 57: Wings.
Unsafe Condition
(e) This AD was prompted by our evaluation of a comment from
David Ligon, Air Tractor, and our determination that we should
reduce the applicability from the all serial numbers beginning with
SN -0001 as required by the previous AD to SN -0001 through SN-0269.
We are issuing this AD to detect and correct cracks in the wing main
spar lower cap at the center splice joint, which could result in
failure of the spar cap and lead to wing separation and loss of
control of the airplane.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
(g) To address this problem for Models AT-802 and AT-802A
airplanes, SNs -0001 through -0091, you must do the following,
unless already done:
Table 1--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Eddy current inspect for Initially inspect Follow Snow
cracks the center splice upon accumulating Engineering Co.
joint outboard two fastener 1,700 hours time-in- Process
holes in both the left and service (TIS) or Specification
right wing main spar lower within the next 50 197, page
caps. hours TIS after 1, revised June 4,
April 21, 2006 (the 2002; pages 2
effective date of through 4, dated
AD 2006-08-09), February 23, 2001;
whichever occurs and page 5, dated
later, and May 3, 2002.
repetitively
thereafter at
intervals not to
exceed 800 hours
TIS. If, before
September 9, 2010
(the effective date
of AD
2010[dash]17[dash]1
8), you installed
the center splice
plate and extended
8-bolt splice
blocks, use the
inspection
compliance times
found in paragraph
(g)(5) of this AD.
(2) If you find any cracks Before further Follow Snow
as a result of any flight after the Engineering Co.
inspection required in inspection where a Service Letter
paragraph (g)(1) of this crack was found. 284, dated
AD, do the following If, before the October 4, 2009;
actions: airplane reaches a Snow Engineering
(i) For cracks that can be total of 3,200 Co. Process
repaired, repair the hours TIS, you Specification
airplane by doing the repair your 197, page
following actions:. airplane following 1, revised June 4,
(A) Install center splice paragraph (g)(2)(i) 2002; pages 2
plate, P/N 20997-2, and of this AD, you through 4, dated
extended 8[dash]bolt splice must do the eddy February 23, 2001;
blocks, P/N 20985-1 & -2, current inspections and page 5, dated
and cold-work the lower following the May 3, 2002; Snow
spar cap fastener holes; compliance times Engineering Co.
and. found in paragraph Drawing Number
(B) Eddy current inspect for (g)(5) of this AD. 20995, Sheet 2,
cracks the center splice If, at 3,200 hours Rev. D., dated
joint outboard two fastener TIS or after, you November 25, 2005;
holes in both the left and repair your and Snow
right wing main spar lower airplane following Engineering Co.
caps. This eddy current paragraph (g)(2)(i) Service Letter
inspection is required as of this AD, this 240, dated
part of the modification repair terminates September 30, 2004.
and is separate from the the inspection
inspections required in requirements of
paragraph (g)(1) of this AD. paragraph (g)(1) of
(ii) For cracks that cannot this AD.
be repaired by
incorporating the
modification specified
above, do the actions to
replace the lower spar caps
and associated parts listed
following the procedures
identified in paragraph
(g)(3) of this AD.
[[Page 82223]]
(3) Replace the wing main (i) Do the Follow Snow
spar lower caps, the web replacement at Engineering Co.
plates, the center joint whichever of the Service Letter
splice blocks and hardware, following 284, dated
and the wing attach angles compliance times October 4, 2009;
and hardware, and install occurs first: Snow Engineering
the steel web splice plate. (A) Before further Co. Service Letter
This replacement terminates flight when cracks 80GG,
the repetitive inspections are found that revised December
required in paragraph cannot be repaired 21, 2005; Snow
(g)(1) of this AD. by incorporating Engineering Co.
the modification in Drawing Number
paragraph (g)(2)(i) 20975, Sheet 4,
of this AD; or. Rev. A, dated
(B) Before or when January 7, 2009.
the airplane
reaches the wing
main spar lower cap
safe life of a
total of 4,100
hours TIS or within
the next 50 hours
TIS after September
9, 2010 (the
effective date of
AD
2010[dash]17[dash]1
8), whichever
occurs later..
(ii) After this
replacement the new
spar safe life is
11,700 hours TIS.
If, before
September 9, 2010
(the effective date
of AD
2010[dash]17[dash]1
8), an airplane
main spar lower cap
was replaced with P/
N 21083-1/-2, the
spar safe life for
that P/N spar cap
is 8,000 hours TIS
until the main spar
lower cap is
replaced with P/N
21118-1/-2. The new
spar safe life for
P/N 21118-1/-2 is
11,700 hours..
(iii) To extend the
initial 4,100 hours
TIS safe life of
the wing main spar
lower cap to a
total of 8,000
hours TIS, you may
incorporate the
optional
modification
specified in
paragraph (g)(4) of
this AD..
(4) To extend the safe life Modify at whichever Follow Snow
of the wing main spar lower of the following Engineering Co.
cap to a total of 8,000 compliance times Service Letter
hours TIS, you may occurs first: 284, dated
incorporate the following (A) Before further October 4, 2009;
optional modification. This flight after any Snow Engineering
modification terminates the inspection required Co. Process
repetitive inspections in paragraph (g)(1) Specification
required in paragraph of this AD where a 197, page
(g)(1) of this AD, unless crack is found. If 1, revised June 4,
you performed the you modify your 2002; pages 2
modification before the airplane before the through 4, dated
airplane reaches a total of airplane reaches a February 23, 2001;
3,200 hours TIS to repair total of 3,200 and page 5, dated
cracks: hours TIS to repair May 3, 2002; Snow
(i) Install center splice cracks as required Engineering Co.
plate, P/N 20997-2, and in paragraph Drawing Number
extended 8[dash]bolt splice (g)(2)(i) of this 20995, Sheet 2,
blocks, P/N 20985-1 & -2, AD, you must do the Rev. D., dated
and cold-work the lower eddy current November 25, 2005;
spar cap fastener holes; inspections and Snow
and. following the Engineering Co.
(ii) Eddy current inspect compliance times Service Letter
for cracks the center found in paragraph 240, dated
splice joint outboard two (g)(5) of this AD.. September 30, 2004.
fastener holes in both the (B) Between 3,200
left and right wing main hours TIS and 4,100
spar lower caps. This eddy hours TIS..
current inspection is
required as part of the
modification and is
separate from the
inspections required in
paragraph (g)(1) of this
AD..
------------------------------------------------------------------------
(5) If, before September 9, 2010 (the effective date of AD
2010-17-18) or as a result of performing the repair for cracks
following paragraph (g)(2) of this AD, you installed the center
splice plate and extended 8-bolt splice blocks, use the following
table for compliance times to do the eddy current inspections
required in paragraph (g)(1) of this AD. If you find any cracks as a
result of any inspection following the compliance times in the
following table, you must do the replacement action in paragraph
(g)(2)(ii) of this AD:
Table 2--Eddy Current Inspection Compliance Times
------------------------------------------------------------------------
Repetitively inspect
thereafter at
Condition of the airplane Initially inspect intervals not to
exceed
------------------------------------------------------------------------
(i) If the airplane has When the airplane 1,200 hours TIS
already had the center reaches a total of until the 8,000
splice plate and extended 2,400 hours TIS hours TIS spar
8[dash]bolt splice blocks after the replacement time.
installed at or after 3,200 modification or
hours TIS but the fastener within the next 100
holes have not been cold days after
worked, at any time you may September 9, 2010
cold work the fastener (the effective date
holes to terminate the of AD
repetitive inspection 2010[dash]17[dash]1
requirements of this 8), whichever
paragraph. occurs later.
(ii) Before reaching 3,200 When the airplane 1,200 hours TIS.
hours TIS, the airplane had reaches a total of Upon reaching 4,800
the center splice plate and 2,400 hours TIS hours TIS after the
extended 8-bolt splice after the modification,
blocks already installed modification or inspect
but the fastener holes have within the next 100 repetitively
not been cold worked. days after thereafter at
September 9, 2010 intervals not to
(the effective date exceed 600 hours
of AD TIS until the 8,000
2010[dash]17[dash]1 hours TIS spar
8), whichever replacement time.
occurs later.
[[Page 82224]]
(iii) Before reaching 3,200 When the airplane 600 hours TIS until
hours TIS, the airplane had reaches a total of the 8,000 hours TIS
the center splice plate and 4,800 hours TIS spar replacement
extended 8-bolt splice after the time.
blocks installed and the modification or
fastener holes have been within the next 100
cold worked. days after
September 9, 2010
(the effective date
of AD
2010[dash]17[dash]1
8), whichever
occurs later.
------------------------------------------------------------------------
(h) To address this problem for AT-802 and AT-802A airplanes,
SNs-0092 through -0101, you must do the following, unless already
done:
Table 3--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Eddy current inspect for Initially inspect Follow Snow
cracks the center splice upon accumulating Engineering Co.
joint outboard two fastener 1,700 hours TIS or Service Letter
holes in both the left and within the next 50 284, dated
right wing main spar lower hours TIS after October 4, 2009;
caps. September 9, 2010 and Snow
(the effective date Engineering Co.
of AD 2010-17-18), Process
whichever occurs Specification
later, and 197, page
repetitively 1, revised June 4,
thereafter at 2002; pages 2
intervals not to through 4, dated
exceed 800 hours February 23, 2001;
TIS. If the center and page 5, dated
splice plate, P/N May 3, 2002.
20994-2, is
installed as
specified in
paragraph (h)(4) of
this AD, do the
repetitive
inspections at
intervals not to
exceed 2,000 hours
TIS.
(2) If you find any cracks Before further Follow Snow
as a result of any flight after the Engineering Co.
inspection required by inspection where a Service Letter
paragraph (h)(1) of this crack was found. 284, dated
AD, do the following This repair October 4, 2009;
actions. This repair modification in and Snow
modification terminates the paragraph (h)(2)(i) Engineering Co.
repetitive inspections of this AD extends Process
required in paragraph the safe life of Specification
(h)(1) of this AD: the wing main spar 197, page
(i) For cracks that can be lower cap to a 1, revised June 4,
repaired, repair the total of 8,000 2002; pages 2
airplane by doing the hours TIS. through 4, dated
following actions:. February 23, 2001;
(A) Install the 9-bolt and page 5, dated
splice blocks and cold-work May 3, 2002, Snow
the lower spar cap fastener Engineering Co.
holes;. Service Letter
(B) Eddy current inspect for 281, dated
cracks the center splice August 1, 2009; and
joint outboard two fastener Snow Engineering
holes in both the left and Co. Drawing Number
right wing main spar lower 20995, Sheet 3,
caps. This eddy current dated November 25,
inspection is required as 2005.
part of the repair and is
separate from the
inspections required in
paragraph (h)(1) of this
AD; and.
(C) Install the center
splice plate, P/N 20994-2,
per paragraph (h)(4) if not
already installed..
(ii) For cracks that cannot
be repaired by doing the
actions in paragraph
(h)(2)(i) of this AD,
replace the lower spar caps
and associated parts listed
following the procedures
identified in paragraph
(h)(3) of this AD..
(3) Replace the wing main (i) Do the Follow Snow
spar lower caps, the web replacement at Engineering Co.
plates, the center joint whichever of the Service Letter
splice blocks and hardware, following 284, dated
and the wing attach angles compliance times October 4, 2009;
and hardware, and install occurs first: Snow Engineering
the steel web splice plate. (A) Before further Co. Service Letter
This replacement terminates flight when cracks 80GG,
the repetitive inspections are found that revised December
required in paragraph cannot be repaired 21, 2005; Snow
(h)(1) of this AD. by incorporating Engineering Co.
the modification in Drawing Number
paragraph (h)(2)(i) 20975, Sheet 4,
of this AD; or. Rev. A, dated
(B) Before or when January 7, 2009.
the airplane
reaches the wing
main spar lower cap
safe life of a
total of 4,100
hours TIS or within
the next 50 hours
TIS after September
9, 2010 (the
effective date of
AD 2010-17-18),
whichever occurs
later..
(ii) To extend the
initial 4,100 hours
TIS safe life of
the wing main spar
lower cap to a
total of 8,000
hours TIS, you may
incorporate the
optional
modification
specified in
paragraph (h)(4) of
this AD..
(iii)After
replacement of the
old spar with the
new lower spar cap,
P/N 21118-1/-2, the
new spar safe life
is 11,700 hours
TIS..
[[Page 82225]]
(4) To extend the safe life Before the airplane Follow Snow
of the wing main spar lower reaches a total of Engineering Co.
cap to a total of 8,000 4,100 hours TIS. Service Letter
hours TIS, you may After installation 284, dated
incorporate the following of the center October 4, 2009;
optional modification: splice plate, P/N Snow Engineering
(i) Install center splice 20994-2, do the Co. Process
plate, P/N 20994-2, if not repetitive Specification
already installed as part inspections 197, page
of a repair, and cold-work required in 1, revised June 4,
the lower spar cap fastener paragraph (h)(1) at 2002; pages 2
holes; and. intervals not to through 4, dated
(ii) Eddy current inspect exceed 2,000 hours February 23, 2001;
for cracks the center TIS. If as of and page 5, dated
splice joint outboard two September 9, 2010 May 3, 2002; Snow
fastener holes in both the (the effective date Engineering Co.
left and right wing main of AD 2010-17-18) Drawing Number
spar lower caps. This eddy you have already 20975, Sheet 4,
current inspection is exceeded the 4,100 Rev. A., dated
required as part of the hours TIS threshold January 7, 2009;
modification and is for extending the and Snow
separate from the safe life to 8,000 Engineering Co.
inspections required in hours TIS, you may Service Letter
paragraph (h)(1) of this be eligible for an 245, dated
AD.. alternative method April 25, 2005.
of compliance
following paragraph
(n) in this AD.
(5) If you find any cracks Before further Follow Snow
as a result of any flight after the Engineering Co.
repetitive inspection inspection where a Service Letter
required by paragraph crack was found. 284, dated
(h)(4) of this AD, do the October 4, 2009;
following actions. This and Snow
repair modification Engineering Co.
terminates the repetitive Process
inspections required in Specification
paragraph (h)(4) of this 197, page
AD: 1, revised June 4,
(i) For cracks that can be 2002; pages 2
repaired, repair the through 4, dated
airplane by doing the February 23, 2001;
following actions:. and page 5, dated
(A) Install the 9-bolt May 3, 2002, Snow
splice blocks and cold-work Engineering Co.
the lower spar cap fastener Service Letter
holes; and. 281, dated
(B) Eddy current inspect for August 1, 2009; and
cracks the center splice Snow Engineering
joint outboard two fastener Co. Drawing Number
holes in both the left and 20995, Sheet 3,
right wing main spar lower dated November 25,
caps. This eddy current 2005.
inspection is required as
part of the repair and is
separate from the
inspections required in
paragraph (h)(1) of this
AD..
(ii) For cracks that cannot
be repaired by doing the
actions in paragraph
(h)(5)(i) of this AD,
replace the lower spar caps
and associated parts listed
following the procedures
identified in paragraph
(h)(3) of this AD..
------------------------------------------------------------------------
(i) To address this problem for AT-802 and AT-802A airplanes,
SNs -0102 through -0178, you must do the following, unless already
done:
Table 4--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Do an initial eddy Before the airplane Follow Snow
current inspection for reaches a total of Engineering Co.
cracks of the center splice 5,500 hours TIS or Process
joint outboard two fastener within the next 50 Specification
holes in both the left and hours TIS after 197, page
right wing main spar lower September 9, 2010 1, revised June 4,
caps. After this initial (the effective date 2002; pages 2
inspection, you may do the of AD through 4, dated
optional cold-working of 2010[dash]17[dash]1 February 23, 2001;
the lower spar cap fastener 8), whichever and page 5, dated
holes to increase the hours occurs later. May 3, 2002; Snow
TIS between repetitive Engineering Co.
inspections required in Service Letter
paragraph (i)(2) of this AD. 245, dated
April 25, 2005; and
Snow Engineering
Co. Service Letter
284, dated
October 4, 2009.
(2) Repetitively eddy (i) For fastener Follow Snow
current inspect for cracks holes that are cold- Engineering Co.
the center splice joint worked: After the Process
outboard two fastener holes initial inspection, Specification
in both the left and right repetitively 197, page
wing main spar lower caps. thereafter inspect 1, revised June 4,
at intervals not to 2002; pages 2
exceed 2,200 hours through 4, dated
TIS. February 23, 2001;
(ii) For fastener and page 5, dated
holes not cold- May 3, 2002; Snow
worked: After the Engineering Co.
initial inspection, Service Letter
repetitively 284, dated
thereafter inspect October 4, 2009;
at intervals not to and (optional) Snow
exceed 1,100 hours Engineering Co.
TIS. Service Letter
245, dated
April 25, 2005.
[[Page 82226]]
(3) If you find any cracks Before further Follow Snow
as a result of any flight after the Engineering Co.
inspection required by inspection where a Service Letter
paragraphs (i)(1) and crack was found. 281, dated
(i)(2) of this AD, do the August 1, 2009; and
following actions. This Snow Engineering
modification terminates the Co. Drawing Number
repetitive inspections 20995, Sheet 3,
required in paragraph dated November 25,
(i)(1) and (i)(2) of this 2005.
AD:
(i) For cracks that can be
repaired, repair the
airplane by doing the
following actions:.
(A) Install the 9-bolt
splice blocks and cold-work
the lower spar cap fastener
holes; and.
(B) Eddy current inspect for
cracks the center splice
joint outboard two fastener
holes in both the left and
right wing main spar lower
caps. This eddy current
inspection is required as
part of the repair and is
separate from the
inspections required in
paragraphs (i)(1) and
(i)(2) of this AD..
(ii) For cracks that cannot
be repaired by doing the
actions in paragraph
(i)(3)(i) of this AD,
replace the lower spar caps
and associated parts listed
following the procedures in
paragraph (i)(4) of this
AD..
(4) Replace the wing main (i) Do the Follow Snow
spar lower caps, the web replacement at Engineering Co.
plates, the center joint whichever of the Service Letter
splice blocks and hardware, following 284, dated
and the wing attach angles compliance times October 4, 2009;
and hardware, and install occurs first: Snow Engineering
the steel web splice plate. (A) Before further Co. Service Letter
This replacement terminates flight when cracks 80GG,
the repetitive inspections are found that revised December
required in paragraphs cannot be repaired 21, 2005; Snow
(i)(1) and (i)(2) of this by incorporating Engineering Co.
AD. the repair in Drawing Number
paragraph (i)(3)(i) 20975, Sheet 4,
of this AD; or. Rev. A, dated
(B) Before or when January 7, 2009.
the airplane
reaches the wing
main spar lower cap
safe life of a
total of 8,000
hours TIS or within
the next 50 hours
TIS after September
9, 2010 (the
effective date of
AD
2010[dash]17[dash]1
8), whichever
occurs later..
(ii) After this
replacement the new
spar safe life is
11,700 hours TIS..
------------------------------------------------------------------------
(j) To address this problem for AT-802 and AT-802A airplanes,
SNs -0179 through -0269, you must do the following, unless already
done:
Table 5--Actions, Compliance, and Procedures
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
Replace the wing main spar By the 8,000 hours Follow Snow
lower caps, the web plates, TIS safe-life or Engineering Co.
the center joint splice within the next 50 Service Letter
blocks and hardware, and hours TIS after 284, dated
the wing attach angles and September 9, 2010 October 4, 2009;
hardware, and install the (the effective date Snow Engineering
steel web splice plate. of AD Co. Service Letter
2010[dash]17[dash]1 80GG,
8), whichever revised December
occurs later. After 21, 2005; Snow
this replacement Engineering Co.
the subsequent new Drawing Number
spar safe life is 20975, Sheet 4,
11,700 hours TIS. Rev. A, dated
January 7, 2009.
------------------------------------------------------------------------
(k) Report any crack from any inspection required in paragraphs
(g), (h), or (i) of this AD within 10 days after the cracks are
found on the form in Figure 1 of this AD.
(1) Send your report to Andrew McAnaul, Aerospace Engineer, ASW-
150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio,
Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370.
(2) The Office of Management and Budget (OMB) approved the
information collection requirements contained in this regulation
under the provisions of the Paperwork Reduction Act and assigned OMB
Control Number 2120-0056.
Special Permit Flight
(l) Under 14 CFR 39.23, we are allowing special flight permits
for the purpose of compliance with this AD under the following
conditions:
(1) Only operate in day visual flight rules (VFR).
(2) Ensure that the hopper is empty.
(3) Limit airspeed to 135 miles per hour (mph) indicated
airspeed (IAS).
(4) Avoid any unnecessary g-forces.
(5) Avoid areas of turbulence.
(6) Plan the flight to follow the most direct route.
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Paperwork Reduction Act Burden Statement
(m) A federal agency may not conduct or sponsor, and a person is
not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Fort Worth Airplane Certification Office,
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD.
(2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards District Office.
(3) AMOCs approved for AD 2010-17-18 are approved as AMOCs for
this AD.
Related Information
(o) For more information about this AD, contact Andrew McAnaul,
Aerospace Engineer, ASW-150 (c/o MIDO-43), 10100 Reunion Place,
Suite 650, San Antonio, Texas 78216; phone: (210) 308-3365; fax:
(210) 308-3370; e-mail: andrew.mcanaul@faa.gov.
Material Incorporated by Reference
(p)(1) You must use the service information contained in table 6
of this AD to do the actions required by this AD, unless the AD
specifies otherwise. The Director of the Federal Register previously
approved the incorporation by reference of the service information
contained in table 6 of this AD on the date specified in the column
``Incorporation by Reference Approval Date'' of Table 6.
Table 6--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Incorporation by reference
Document Revision Date approval date
----------------------------------------------------------------------------------------------------------------
(i) Snow Engineering Co. Service Not Applicable........ December 21, 2005..... September 9, 2010 (75 FR
Letter 80GG. 52255, August 25, 2010).
(ii) Snow Engineering Co. Service Not Applicable........ October 4, 2009....... September 9, 2010 (75 FR
Letter 284. 52255, August 25, 2010).
(iii) Snow Engineering Co. Service Not Applicable........ August 1, 2009........ September 9, 2010 (75 FR
Letter 281. 52255, August 25, 2010).
(iv) Snow Engineering Co. Service Not Applicable........ April 25, 2005........ September 9, 2010 (75 FR
Letter 245. 52255, August 25, 2010).
(v) Snow Engineering Co. Service Not Applicable........ September 30, 2004.... April 21, 2006 (71 FR
Letter 240. 19994, April 19, 2006).
(vi) Snow Engineering Co. Process ...................... ...................... April 21, 2006 (71 FR
Specification 197: 19994, April 19, 2006).
page 1......................... Not Applicable........ June 4, 2002.......... April 21, 2006 (71 FR
19994, April 19, 2006).
pages 2 through 4.............. Not Applicable........ February 23, 2001..... April 21, 2006 (71 FR
19994, April 19, 2006).
page 5......................... Not Applicable........ May 3, 2002........... April 21, 2006 (71 FR
19994, April 19, 2006).
(vii) Snow Engineering Co. Drawing ...................... ...................... September 9, 2010 (75 FR
Number 20995: 52255, August 25, 2010).
Sheet 2........................ Rev. D................ November 25, 2005..... September 9, 2010 (75 FR
52255, August 25, 2010).
Sheet 3........................ Not Applicable........ November 25, 2005..... September 9, 2010 (75 FR
52255, August 25, 2010).
(viii) Snow Engineering Co. Drawing Rev. A................ January 7, 2009....... September 9, 2010 (75 FR
Number 20975, Sheet 4. 52255, August 25, 2010).
----------------------------------------------------------------------------------------------------------------
(2) For service information identified in this AD, contact Air
Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940)
564-5616; fax: (940) 564-5612; E-mail: airmail@airtractor.com;
Internet: www.airtractor.com.
(3) You may review copies of the service information at the FAA,
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106.
For information on the availability of this material at the FAA,
call 816-329-4148.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on December 16, 2010.
William J. Timberlake,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-32905 Filed 12-29-10; 8:45 am]
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