Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes, 39243-39247 [E9-18815]
Download as PDF
<![CDATA[
Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules
and novel aircraft can be evaluated, and
the effects of aircraft configuration
changes may be observed and measured.
A Flying Qualities Demonstrator would
enable the use of aircraft with modified
flight controls to be used in the
demonstration and development of
flying qualities and flight controls. It is
impractical to certificate these modified
aircraft in compliance with the
requirements of their standard category
type certificate. Approval of these flight
operations will be in compliance with
the restricted category operating
limitations specified in 14 CFR 91.313.
How To Obtain Copies:
You may get a copy of our proposal
from the Internet at: https://www.faa.gov/
aircraft/draft_docs/.
You may also request a copy from Mr.
Graham Long. See the section entitled
FOR FURTHER INFORMATION CONTACT for
the complete address.
Issued in Washington, DC, on July 24,
2009.
Susan J. M. Cabler,
Assistant Manager, Aircraft Engineering
Division, Aircraft Certification Service.
[FR Doc. E9–18573 Filed 8–5–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0707; Directorate
Identifier 2009–CE–035–AD]
RIN 2120–AA64
Airworthiness Directives; Air Tractor,
Inc. Models AT–802 and AT–802A
Airplanes
jlentini on DSKJ8SOYB1PROD with PROPOSALS
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to supersede
Airworthiness Directive (AD) 2006–08–
09, which applies to all Air Tractor, Inc.
(Air Tractor) Models AT–802 and AT–
802A airplanes. AD 2006–08–09
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 cap. Since
we issued AD 2006–08–09, we have
determined we need to clarify the
applicability of Models AT–802 and
AT–802A airplanes affected serial
number (SN) ranges. Additionally, we
propose to add an option of modifying
VerDate Nov<24>2008
15:55 Aug 05, 2009
Jkt 217001
the wing main spar lower caps to extend
the safe life limit on the affected
airplanes. Consequently, this proposed
AD would keep the actions of AD 2006–
08–09, clarify the applicability of
Models AT–802 and AT–802A affected
SN ranges, and add a modification
option to extend the safe life limit. We
are proposing 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: We must receive comments on
this proposed AD by September 21,
2009.
Use one of the following
addresses to comment on this proposed
AD:
• 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–
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 proposed 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.
FOR FURTHER INFORMATION CONTACT:
Andy McAnaul, Aerospace Engineer,
ASW–150, FAA San Antonio MIDO–43,
10100 Reunion Pl., Ste. 650, San
Antonio, Texas 78216; telephone: (210)
308–3365; fax: (210) 308–3370.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number, ‘‘FAA–2009–0707; Directorate
Identifier 2009–CE–035–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
39243
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
concerning this proposed AD.
Discussion
Since 2000, we have issued several
airworthiness directives (ADs) related to
the wing spar inspection and safe life on
Air Tractor AT–400, AT–500, AT–600,
and AT–800 series airplanes.
In 2001, we issued AD 2001–10–04,
Amendment 39–12230 (66 FR 27014,
May 16, 2001) to lower the safe life for
the wing lower spar cap on Air Tractor
AT–400, AT–500, and AT–800 series
airplanes. This AD allowed for
inspection (using eddy current methods)
of the wing lower spar cap for airplanes
that were at or over the lower safe life
and for which parts were not available.
Later that same year we revised that AD
to remove AT–800 series airplanes from
the applicability that were equipped
with the factory-supplied computerized
fire gate (part number 80540) and
engaged in full-time firefighting.
In 2002, we issued AD 2002–11–05,
Amendment 39–12766 (67 FR 37967,
May 31, 2002) to further reduce the safe
life for certain AT–400 series airplanes
and certain AT–500 series airplanes that
either incorporate or have incorporated
Marburger winglets.
After receiving reports of fatigue
cracking found on three Model AT–
802A airplanes that were below the
reduced safe life established in AD
2002–11–05, we issued AD 2006–08–09,
Amendment 39–14565 (71 FR 27784,
May 12, 2006). AD 2006–08–09
currently requires the following on Air
Tractor Models AT–802 and AT–802A
airplanes:
• Repetitively inspecting (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
• Repairing or replacing any cracked
spar cap.
Since we issued AD 2006–08–09, we
have determined we need to clarify the
applicability of Models AT–802 and
AT–802A airplanes affected SN ranges.
The manufacturer, Air Tractor, shared a
common SN range for the Models AT–
802 and AT–802A. Sometimes service
information listed only one of the
models with a starting or ending SN
within an SN range, depending on
which model was produced with that
specific SN, even though the service
information applied to both models.
Additionally, we propose to add an
option of modifying the wing main spar
E:\FR\FM\06AUP1.SGM
06AUP1
39244
Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules
lower caps to extend the safe life limit
on the affected airplanes.
This condition, if not corrected, could
result in failure of the spar cap and lead
to wing separation and loss of control of
the airplane.
Relevant Service Information
We have reviewed the following
Snow Engineering Co. service
information:
• Process Specification #197, page 1,
revised June 4, 2002; pages 2 through 4,
dated February 23, 2001; and page 5,
dated May 3, 2002;
• Process Specification #204, Rev. C,
dated November 16, 2004;
• Service Letter #215, page 5, titled
‘‘802 Spar Inspection Holes and Vent
Tube Mod,’’ dated November 19, 2003;
• Service Letter #240, dated
September 30, 2004;
• Service Letter #244, dated April 25,
2005;
• Drawing Number 20975, Sheet 2,
Rev. A, dated September 1, 2004;
• Drawing Number 20975, Sheet 3,
dated January 6, 2005; and
• Drawing Number 20995, Sheet 2,
Rev. C., dated September 28, 2004.
The service information describes
procedures for:
• Repetitively inspecting (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
• Repairing or replacing any cracked
spar cap.
FAA’s Determination and Requirements
of the Proposed AD
We are proposing this AD because we
evaluated all information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This proposed AD would
supersede AD 2006–08–09 with a new
AD that would incorporate the actions
in the previously-referenced service
information. This proposed AD would
require you to use the service
information described previously to
perform these actions.
Differences Between This Proposed AD
and the Service Information
Sometimes service information lists
only one of the models with a starting
or ending SN within an SN range,
depending on which of those models
was produced with that SN, even
though the service information applies
to both models. The requirements of this
proposed AD, if adopted as a final rule,
would take precedence over the
provisions in the service information.
Costs of Compliance
We estimate that this proposed AD
would affect 187 airplanes in the U.S.
registry.
We estimate the following costs to do
the proposed inspection:
Labor cost
Parts cost
Total cost per airplane
$500 to $800 ..................................
Not applicable ...............................
$500 to $800 ................................
We estimate the following costs to do
any necessary repairs for two spars that
may be required based on the results of
the proposed inspection or the
modification as an option. We have no
Total cost on U.S. operators
$93,500 to $149,600.
way of determining the number of
airplanes that may need this repair:
Parts cost
(two spars)
Labor cost (two spars)
225 work-hours × $80 per hour = $18,000 .....................................................................................................................
We estimate the following costs to do
any necessary spar cap replacement
(two spars) that would be required
based on the results of the proposed
inspection. We have no way of
jlentini on DSKJ8SOYB1PROD with PROPOSALS
15:55 Aug 05, 2009
Jkt 217001
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
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
PO 00000
Frm 00015
Fmt 4702
$25,500
Parts cost
(two spars)
495 work-hours × $80 per hour = $39,600 .....................................................................................................................
VerDate Nov<24>2008
$7,500
determining the number of airplanes
that may need this replacement:
Labor cost (two spars)
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
Total cost
(two spars)
per airplane
Sfmt 4702
Total cost
(two spars)
per airplane
$39,100
$78,700
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 the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
E:\FR\FM\06AUP1.SGM
06AUP1
Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the proposed AD, the
regulatory evaluation, any comments
received, and other information 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 Docket Office (telephone
(800) 647–5527) is located at the street
address stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2006–08–09, Amendment 39–14565 (71
FR 27784, May 12, 2006), and adding
the following new AD:
Air Tractor, Inc.: Docket No. FAA–2009–
0707; Directorate Identifier 2009–CE–
035–AD.
Comments Due Date
(a) We must receive comments on this
airworthiness directive (AD) action by
September 21, 2009.
Affected ADs
(b) This AD supersedes AD 2006–08–09,
Amendment 39–14565.
Applicability
(c) This AD affects Model AT–802 and AT–
802A airplanes, all serial numbers (SNs)
beginning with –0001, 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.
39245
Unsafe Condition
(d) This AD results from our determination
that we need to clarify the applicability of
Models AT–802 and AT–802A airplanes
affected serial number (SN) ranges.
Additionally, we are adding an option to
modify the wing main spar lower caps to
extend the safe life limit on the affected
airplanes. 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
(e) For Models AT–802 and AT–802A
airplanes, SNs –0001 through –0091, do the
following actions, unless already done, using
the wing main spar lower cap hours time-inservice (TIS) schedule found in Table 1 of
this AD to do the initial and repetitive
inspections:
(1) Install access cover plates following
Snow Engineering Co. Service Letter #215,
page 5, titled ‘‘802 Spar Inspection Holes and
Vent Tube Mod,’’ dated November 19, 2003.
(2) Eddy current inspect for cracks the
center splice joint outboard two fastener
holes in both the right and left wing main
spar lower caps following 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.
TABLE 1—INSPECTION TIMES
Repetitively inspect
thereafter at intervals
not to exceed
Condition
Initially inspect
(i) AT–802 and AT–802A, SNs
–0001 through –0091.
As manufactured ........................
(ii) AT–802 and AT–802A, serial
numbers SNs –0001 through
–0091.
jlentini on DSKJ8SOYB1PROD with PROPOSALS
SNs
Modified with cold-worked fastener holes following Service
Letter #244, dated April 25,
2005.
Upon accumulating 1,700 hours TIS after
April 21, 2006 (the effective date of AD
2006–08–09) or within the next 50 hours
TIS after April 21, 2006 (the effective
date of AD 2006–08–09), whichever occurs later.
If performing the cold-working procedure in
Service Letter #244, dated April 25,
2005, it includes the initial eddy current
inspection.
(f) One of the following must do the eddy
current inspections required in paragraph
(e)(2) of this AD:
(1) A level 2 or 3 inspector certified in
eddy current inspection using the guidelines
established by the American Society for
Nondestructive Testing or MIL–STD–410; or
(2) A person authorized to perform AD
work and who has completed and passed the
Air Tractor, Inc. training course on eddy
current inspection on wing lower spar caps.
(g) If cracks are found during any
inspection required in paragraph (e)(2) of this
AD, repair or replace any cracked spar cap
before further flight after the inspection in
which cracks are found. For repair or
replacement, do whichever of the following
that applies:
VerDate Nov<24>2008
15:55 Aug 05, 2009
Jkt 217001
(1) For cracks that can be repaired by
incorporating the modification specified in
paragraph (j) of this AD, do the actions
following the procedures in paragraph (j) of
this AD before further flight after the
inspection in which cracks are found.
(2) For cracks that cannot be repaired by
incorporating the modification specified in
paragraph (j) of this AD, replace the lower
spar caps and associated parts listed
following the procedures identified in
paragraph (h) of this AD before further flight
after the inspection in which cracks are
found.
(h) For all AT–802 and AT–802A airplanes,
replace the wing main spar lower caps, the
center joint splice blocks and hardware, the
wing attach angles and hardware, and install
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
850 hours TIS.
1,700 hours TIS.
the steel web splice plate (P/N 21106–1 for
SNs –0001 through –0091, and P/N 20094–
2 for all SNs beginning with –0092). Do the
replacement upon accumulating the safe life
hours TIS on the wing main spar lower caps
as listed in Table 2 of this AD or within 50
hours TIS after April 21, 2006 (the effective
date of AD 2006–08–09), whichever occurs
later. For SNs –0001 through –0091, you may
extend the safe life hours TIS of the wing
main spar lower caps to 8,000 hours TIS
before doing the replacement if you modified
your wing as specified in paragraph (j) of this
AD.
(1) Use the following service information
for replacement:
(i) For airplane Models AT–802 and AT–
802A, SNs –0001 through –0091, follow
E:\FR\FM\06AUP1.SGM
06AUP1
39246
Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules
Snow Engineering Co. Drawing Number
20975, Sheet 3, dated January 6, 2005; and
Process Specification #204, Rev. C, dated
November 16, 2004.
(ii) For airplane Models AT–802 and AT–
802A, SNs beginning with –0092, follow
Drawing Number 20975, Sheet 2, Rev. A,
dated September 1, 2004; and Process
Specification #204, Rev. C, dated November
16, 2004.
(2) The following presents the safe life and
replacement times as required in paragraph
(h) of this AD:
TABLE 2—SAFE LIFE AND REPLACEMENT TIMES
SNs
Wing spar lower cap safe life
AT–802–0001 through AT–802–0059 ..........................................................................................................
AT–802–0060 through AT–802–0091 ..........................................................................................................
All beginning with AT–802–0092 ..................................................................................................................
AT–802A–0001 through AT–802A–0059 .....................................................................................................
AT–802A–0060 through AT–802A–0091 .....................................................................................................
All beginning with AT–802A–0092 ...............................................................................................................
(i) After replacing the wing main spar
lower caps and hardware, installing the web
splice plate, and cold working the fastener
holes by following Snow Engineering Co.
Drawing Number 20975, Sheet 3, dated
January 6, 2005 (SNs –0001 through –0091);
or Sheet 2, Rev. A, dated September 1, 2004
(all SNs beginning with –0092); and Process
4,132
4,188
8,163
4,969
4,531
8,648
hours
hours
hours
hours
hours
hours
TIS.
TIS.
TIS.
TIS.
TIS.
TIS.
Specification #204, Rev. C, dated November
16, 2004, the new safe life for the wing main
spar lower caps is as follows:
TABLE 3—NEW SAFE LIFE FOR WING MAIN SPAR LOWER CAPS
SNs
Wing spar lower cap safe life
jlentini on DSKJ8SOYB1PROD with PROPOSALS
All beginning with AT–802–0001 ..................................................................................................................
All beginning with AT–802A–0001 ...............................................................................................................
(j) For Models AT–802 and AT–802A
airplanes, SNs –0001 through –0091, in lieu
of replacing the wing main spar lower cap at
the safe life hours TIS listed in Table 2 in
paragraph (h) of this AD, you may extend the
safe life of the wing main spar lower caps by
doing the following actions. Between 3,200
hours TIS and the safe life hours TIS for your
airplane currently listed in Table 2 of this
AD, do the following, unless already done:
(1) Modify the wing by installing P/N
20997–2 web plate and P/N 20985–1 and
20985–2 extended 8-bolt splice blocks
following Snow Engineering Co. Drawing
20995, Sheet 2, Rev. C, dated September 28,
2004.
(2) Cold-work the outboard two fastener
holes in both the left and right hand lower
spar caps at the center splice following Snow
Engineering Co. Service Letter #240, dated
September 30, 2004.
(3) Do an eddy current inspection of the
wing center splice joint outboard two
fastener holes in both the right and left wing
main spar lower caps for cracks at the time
of modification following 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.
(4) If, before the effective date of this AD,
an airplane has already been modified
following paragraph (j)(1) of this AD but did
not receive cold working in the outboard two
fastener holes in both the left and right hand
lower spar caps following paragraph (j)(2) of
this AD, do the following:
(i) Initially do an eddy current inspection
within the next 2,400 hours TIS after the
modification, using the procedure in
paragraph (j)(3) of this AD, and repetitively
thereafter at intervals not to exceed every
1,200 hours TIS until the wing spar lower
cap reaches 8,000-hour TIS safe life.
VerDate Nov<24>2008
15:55 Aug 05, 2009
Jkt 217001
(ii) At any time after the modification, you
may do the cold working in the outboard two
fastener holes in both the left and right hand
lower spar caps following paragraph (j)(2) of
this AD to terminate the repetitive eddy
current inspections required in paragraph
(j)(4)(i) of this AD.
(5) If you have modified your airplane
following paragraph (j)(1) of this AD prior to
3,200 hours TIS, you must do the following
to reach the extended 8,000-hour TIS safe
life:
(i) If you did not cold work in the outboard
two fastener holes in both the left and right
hand lower spar caps following paragraph
(j)(2) of this AD, you must do the repetitive
eddy current inspections following paragraph
(j)(4)(i) of this AD until you accumulate 4,800
hours TIS after the modification on the wing
spar lower cap. Upon accumulation of 4,800
hours TIS after the modification on the wing
spar lower cap, do the repetitive eddy current
inspections at intervals not to exceed every
600 hours TIS until you reach the extended
safe life of 8,000-hour TIS.
(ii) If you did cold work the outboard two
fastener holes in both the left and right hand
lower spar caps following paragraph (j)(2) of
this AD, upon accumulation of 4,800 hours
TIS after the modification on the wing spar
lower cap do the repetitive eddy current
inspections at intervals not to exceed every
600 hours TIS until you reach the 8,000-hour
TIS safe life.
(6) For the initial and repetitive eddy
current inspections required in paragraphs
(j)(3), (j)(4)(i), (j)(5)(i) and (j)(5)(ii) of this AD,
follow the instructions as specified in 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. For any cracks found, follow
the instructions for repair or replacement as
specified in paragraph (g) of this AD.
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
8,163 hours TIS.
8,648 hours TIS.
(k) If any cracks are found as a result of any
inspection required in paragraphs (e)(2),
(j)(3), (j)4)(i), (j)(5)(i), and (j)(5)(ii) of this AD,
report any cracks you find within 10 days
after the cracks are found or within 10 days
after April 21, 2006 (the effective date of AD
2006–08–09), whichever occurs later.
(1) Include in your report the aircraft SN,
aircraft hours TIS, wing spar cap hours TIS,
crack location and size, corrective action
taken, and a point of contact name and phone
number. Send your report to Andrew
McAnaul, Aerospace Engineer, ASW–150
(c/o MIDO–43), 10100 Reunion Place, Suite
650, San Antonio, Texas 78216; telephone:
(210) 308–3365; facsimile: (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 part 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.
Alternative Methods of Compliance
(AMOCs)
(m) The Manager, Fort Worth Airplane
Certification Office, ASW–150, FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
E:\FR\FM\06AUP1.SGM
06AUP1
Federal Register / Vol. 74, No. 150 / Thursday, August 6, 2009 / Proposed Rules
CFR 39.19. Send information to ATTN: Andy
McAnaul, Aerospace Engineer, ASW–150,
FAA San Antonio MIDO–43, 10100 Reunion
Pl., Ste. 650, San Antonio, Texas 78216;
telephone: (210) 308–3365; fax: (210) 308–
3370. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(n) AMOCs approved for AD 2006–08–09
are not approved for this AD.
Related Information
(o) To get copies of the service information
referenced 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. To view the
AD docket, go to U.S. Department of
Transportation, Docket Operations, M–30,
West Building Ground Floor, Room W12–
140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, or on the Internet at
https://www.regulations.gov.
2009–0319 using any one of the
following methods:
(1) Federal eRulemaking Portal:
https://www.regulations.gov.
(2) Fax: 202–493–2251.
(3) Mail: Docket Management Facility
(M–30), U.S. Department of
Transportation, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590–
0001.
(4) Hand delivery: Same as mail
address above, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The telephone number
is 202–366–9329.
To avoid duplication, please use only
one of these four methods. See the
‘‘Public Participation and Request for
Comments’’ portion of the
SUPPLEMENTARY INFORMATION section
below for instructions on submitting
comments.
DEPARTMENT OF HOMELAND
SECURITY
FOR FURTHER INFORMATION CONTACT: If
you have questions on this proposed
rule, call or e-mail Petty Officer Shane
Jackson, Waterways Management, U.S.
Coast Guard Sector San Diego at
telephone 619–278–7262, e-mail
Shane.E.Jackson@uscg.mil. If you have
questions on viewing or submitting
material to the docket, call Renee V.
Wright, Program Manager, Docket
Operations, telephone 202–366–9826.
SUPPLEMENTARY INFORMATION:
Coast Guard
Public Participation and Request for
Comments
Issued in Kansas City, Missouri, on July 31,
2009.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–18815 Filed 8–5–09; 8:45 am]
BILLING CODE 4910–13–P
33 CFR Part 165
[Docket No. USCG–2009–0319]
RIN 1625–AA00
Safety Zone; Sea World December
Fireworks, Mission Bay, San Diego, CA
Coast Guard, DHS.
Notice of proposed rulemaking.
AGENCY:
jlentini on DSKJ8SOYB1PROD with PROPOSALS
ACTION:
SUMMARY: The Coast Guard proposes to
establish a safety zone upon the
navigable waters of Mission Bay near
San Diego, California in support of the
Sea World December Fireworks. This
safety zone is necessary to provide for
the safety of the participants, crew,
spectators, participating vessels, and
other users of the waterway. Persons
and vessels are prohibited from entering
into, transiting through, or anchoring
within this safety zone unless
authorized by the Captain of the Port, or
his designated representative.
DATES: Comments and related material
must be received by the Coast Guard on
or before September 8, 2009.
ADDRESSES: You may submit comments
identified by docket number USCG–
VerDate Nov<24>2008
15:55 Aug 05, 2009
Jkt 217001
We encourage you to participate in
this rulemaking by submitting
comments and related materials. All
comments received will be posted
without change to https://
www.regulations.gov and will include
any personal information you have
provided.
Submitting Comments
If you submit a comment, please
include the docket number for this
rulemaking (USCG–2009–0319),
indicate the specific section of this
document to which each comment
applies, and provide a reason for each
suggestion or recommendation. You
may submit your comments and
material online (via https://
www.regulations.gov) or by fax, mail, or
hand delivery, but please use only one
of these means. If you submit a
comment online via https://
www.regulations.gov, it will be
considered received by the Coast Guard
when you successfully transmit the
comment. If you fax, hand deliver, or
mail your comment, it will be
considered as having been received by
the Coast Guard when it is received at
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
39247
the Docket Management Facility. We
recommend that you include your name
and a mailing address, an e-mail
address, or a telephone number in the
body of your document so that we can
contact you if we have questions
regarding your submission.
To submit your comment online, go to
https://www.regulations.gov, select the
Advanced Docket Search option on the
right side of the screen, insert ‘‘USCG–
2009–0319’’ in the Docket ID box, press
Enter, and then click on the balloon
shape in the Actions column. If you
submit your comments by mail or hand
delivery, submit them in an unbound
format, no larger than 81⁄2 by 11 inches,
suitable for copying and electronic
filing. If you submit comments by mail
and would like to know that they
reached the Facility, please enclose a
stamped, self-addressed postcard or
envelope. We will consider all
comments and material received during
the comment period and may change
the rule based on your comments.
Viewing Comments and Documents
To view comments, as well as
documents mentioned in this preamble
as being available in the docket, go to
https://www.regulations.gov, select the
Advanced Docket Search option on the
right side of the screen, insert USCG–
2009–0319 in the Docket ID box, press
Enter, and then click on the item in the
Docket ID column. You may also visit
the Docket Management Facility in
Room W12–140 on the ground floor of
the Department of Transportation West
Building, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. We have an
agreement with the Department of
Transportation to use the Docket
Management Facility.
Privacy Act
Anyone can search the electronic
form of comments received into any of
our dockets by the name of the
individual submitting the comment (or
signing the comment, if submitted on
behalf of an association, business, labor
union, etc.). You may review a Privacy
Act notice regarding our public dockets
in the January 17, 2008 issue of the
Federal Register (73 FR 3316).
Public Meeting
We do not now plan to hold a public
meeting. But you may submit a request
for one using one of the four methods
specified under ADDRESSES. Please
explain why you believe a public
meeting would be beneficial. If we
determine that one would aid this
rulemaking, we will hold one at a time
E:\FR\FM\06AUP1.SGM
06AUP1
]]>Agencies
[Federal Register Volume 74, Number 150 (Thursday, August 6, 2009)]
[Proposed Rules]
[Pages 39243-39247]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-18815]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0707; Directorate Identifier 2009-CE-035-AD]
RIN 2120-AA64
Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-
802A Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2006-08-
09, which applies to all Air Tractor, Inc. (Air Tractor) Models AT-802
and AT-802A airplanes. AD 2006-08-09 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 cap.
Since we issued AD 2006-08-09, we have determined we need to clarify
the applicability of Models AT-802 and AT-802A airplanes affected
serial number (SN) ranges. Additionally, we propose to add an option of
modifying the wing main spar lower caps to extend the safe life limit
on the affected airplanes. Consequently, this proposed AD would keep
the actions of AD 2006-08-09, clarify the applicability of Models AT-
802 and AT-802A affected SN ranges, and add a modification option to
extend the safe life limit. We are proposing 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: We must receive comments on this proposed AD by September 21,
2009.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
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-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 proposed 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.
FOR FURTHER INFORMATION CONTACT: Andy McAnaul, Aerospace Engineer, ASW-
150, FAA San Antonio MIDO-43, 10100 Reunion Pl., Ste. 650, San Antonio,
Texas 78216; telephone: (210) 308-3365; fax: (210) 308-3370.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2009-0707; Directorate Identifier 2009-CE-035-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light 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 concerning this proposed AD.
Discussion
Since 2000, we have issued several airworthiness directives (ADs)
related to the wing spar inspection and safe life on Air Tractor AT-
400, AT-500, AT-600, and AT-800 series airplanes.
In 2001, we issued AD 2001-10-04, Amendment 39-12230 (66 FR 27014,
May 16, 2001) to lower the safe life for the wing lower spar cap on Air
Tractor AT-400, AT-500, and AT-800 series airplanes. This AD allowed
for inspection (using eddy current methods) of the wing lower spar cap
for airplanes that were at or over the lower safe life and for which
parts were not available. Later that same year we revised that AD to
remove AT-800 series airplanes from the applicability that were
equipped with the factory-supplied computerized fire gate (part number
80540) and engaged in full-time firefighting.
In 2002, we issued AD 2002-11-05, Amendment 39-12766 (67 FR 37967,
May 31, 2002) to further reduce the safe life for certain AT-400 series
airplanes and certain AT-500 series airplanes that either incorporate
or have incorporated Marburger winglets.
After receiving reports of fatigue cracking found on three Model
AT-802A airplanes that were below the reduced safe life established in
AD 2002-11-05, we issued AD 2006-08-09, Amendment 39-14565 (71 FR
27784, May 12, 2006). AD 2006-08-09 currently requires the following on
Air Tractor Models AT-802 and AT-802A airplanes:
Repetitively inspecting (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
Repairing or replacing any cracked spar cap.
Since we issued AD 2006-08-09, we have determined we need to
clarify the applicability of Models AT-802 and AT-802A airplanes
affected SN ranges. The manufacturer, Air Tractor, shared a common SN
range for the Models AT-802 and AT-802A. Sometimes service information
listed only one of the models with a starting or ending SN within an SN
range, depending on which model was produced with that specific SN,
even though the service information applied to both models.
Additionally, we propose to add an option of modifying the wing
main spar
[[Page 39244]]
lower caps to extend the safe life limit on the affected airplanes.
This condition, if not corrected, could result in failure of the
spar cap and lead to wing separation and loss of control of the
airplane.
Relevant Service Information
We have reviewed the following Snow Engineering Co. service
information:
Process Specification 197, page 1, revised June
4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated
May 3, 2002;
Process Specification 204, Rev. C, dated November
16, 2004;
Service Letter 215, page 5, titled ``802 Spar
Inspection Holes and Vent Tube Mod,'' dated November 19, 2003;
Service Letter 240, dated September 30, 2004;
Service Letter 244, dated April 25, 2005;
Drawing Number 20975, Sheet 2, Rev. A, dated September 1,
2004;
Drawing Number 20975, Sheet 3, dated January 6, 2005; and
Drawing Number 20995, Sheet 2, Rev. C., dated September
28, 2004.
The service information describes procedures for:
Repetitively inspecting (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
Repairing or replacing any cracked spar cap.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This proposed AD
would supersede AD 2006-08-09 with a new AD that would incorporate the
actions in the previously-referenced service information. This proposed
AD would require you to use the service information described
previously to perform these actions.
Differences Between This Proposed AD and the Service Information
Sometimes service information lists only one of the models with a
starting or ending SN within an SN range, depending on which of those
models was produced with that SN, even though the service information
applies to both models. The requirements of this proposed AD, if
adopted as a final rule, would take precedence over the provisions in
the service information.
Costs of Compliance
We estimate that this proposed AD would affect 187 airplanes in the
U.S. registry.
We estimate the following costs to do the proposed inspection:
----------------------------------------------------------------------------------------------------------------
Total cost on U.S.
Labor cost Parts cost Total cost per airplane operators
----------------------------------------------------------------------------------------------------------------
$500 to $800......................... Not applicable......... $500 to $800........... $93,500 to $149,600.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs for
two spars that may be required based on the results of the proposed
inspection or the modification as an option. We have no way of
determining the number of airplanes that may need this repair:
------------------------------------------------------------------------
Total cost
Parts cost (two spars)
Labor cost (two spars) (two spars) per
airplane
------------------------------------------------------------------------
225 work-hours x $80 per hour = $18,000....... $7,500 $25,500
------------------------------------------------------------------------
We estimate the following costs to do any necessary spar cap
replacement (two spars) that would be required based on the results of
the proposed inspection. We have no way of determining the number of
airplanes that may need this replacement:
------------------------------------------------------------------------
Total cost
Parts cost (two spars)
Labor cost (two spars) (two spars) per
airplane
------------------------------------------------------------------------
495 work-hours x $80 per hour = $39,600....... $39,100 $78,700
------------------------------------------------------------------------
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
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
[[Page 39245]]
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information 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 Docket Office (telephone (800) 647-5527)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive
(AD) 2006-08-09, Amendment 39-14565 (71 FR 27784, May 12, 2006), and
adding the following new AD:
Air Tractor, Inc.: Docket No. FAA-2009-0707; Directorate Identifier
2009-CE-035-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by September 21, 2009.
Affected ADs
(b) This AD supersedes AD 2006-08-09, Amendment 39-14565.
Applicability
(c) This AD affects Model AT-802 and AT-802A airplanes, all
serial numbers (SNs) beginning with -0001, 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.
Unsafe Condition
(d) This AD results from our determination that we need to
clarify the applicability of Models AT-802 and AT-802A airplanes
affected serial number (SN) ranges. Additionally, we are adding an
option to modify the wing main spar lower caps to extend the safe
life limit on the affected airplanes. 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
(e) For Models AT-802 and AT-802A airplanes, SNs -0001 through -
0091, do the following actions, unless already done, using the wing
main spar lower cap hours time-in-service (TIS) schedule found in
Table 1 of this AD to do the initial and repetitive inspections:
(1) Install access cover plates following Snow Engineering Co.
Service Letter 215, page 5, titled ``802 Spar Inspection
Holes and Vent Tube Mod,'' dated November 19, 2003.
(2) Eddy current inspect for cracks the center splice joint
outboard two fastener holes in both the right and left wing main
spar lower caps following 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.
Table 1--Inspection Times
----------------------------------------------------------------------------------------------------------------
Repetitively inspect thereafter at
SNs Condition Initially inspect intervals not to exceed
----------------------------------------------------------------------------------------------------------------
(i) AT-802 and AT-802A, SNs - As manufactured... Upon accumulating 850 hours TIS.
0001 through -0091. 1,700 hours TIS after
April 21, 2006 (the
effective date of AD
2006-08-09) or within
the next 50 hours TIS
after April 21, 2006
(the effective date
of AD 2006-08-09),
whichever occurs
later.
(ii) AT-802 and AT-802A, serial Modified with If performing the 1,700 hours TIS.
numbers SNs -0001 through - cold[dash]worked cold[dash]working
0091. fastener holes procedure in Service
following Service Letter 244,
Letter 244, dated it includes the
April 25, 2005. initial eddy current
inspection.
----------------------------------------------------------------------------------------------------------------
(f) One of the following must do the eddy current inspections
required in paragraph (e)(2) of this AD:
(1) A level 2 or 3 inspector certified in eddy current
inspection using the guidelines established by the American Society
for Nondestructive Testing or MIL-STD-410; or
(2) A person authorized to perform AD work and who has completed
and passed the Air Tractor, Inc. training course on eddy current
inspection on wing lower spar caps.
(g) If cracks are found during any inspection required in
paragraph (e)(2) of this AD, repair or replace any cracked spar cap
before further flight after the inspection in which cracks are
found. For repair or replacement, do whichever of the following that
applies:
(1) For cracks that can be repaired by incorporating the
modification specified in paragraph (j) of this AD, do the actions
following the procedures in paragraph (j) of this AD before further
flight after the inspection in which cracks are found.
(2) For cracks that cannot be repaired by incorporating the
modification specified in paragraph (j) of this AD, replace the
lower spar caps and associated parts listed following the procedures
identified in paragraph (h) of this AD before further flight after
the inspection in which cracks are found.
(h) For all AT-802 and AT-802A airplanes, replace the wing main
spar lower caps, the center joint splice blocks and hardware, the
wing attach angles and hardware, and install the steel web splice
plate (P/N 21106-1 for SNs -0001 through -0091, and P/N 20094-2 for
all SNs beginning with -0092). Do the replacement upon accumulating
the safe life hours TIS on the wing main spar lower caps as listed
in Table 2 of this AD or within 50 hours TIS after April 21, 2006
(the effective date of AD 2006-08-09), whichever occurs later. For
SNs -0001 through -0091, you may extend the safe life hours TIS of
the wing main spar lower caps to 8,000 hours TIS before doing the
replacement if you modified your wing as specified in paragraph (j)
of this AD.
(1) Use the following service information for replacement:
(i) For airplane Models AT-802 and AT-802A, SNs -0001 through -
0091, follow
[[Page 39246]]
Snow Engineering Co. Drawing Number 20975, Sheet 3, dated January 6,
2005; and Process Specification 204, Rev. C, dated November
16, 2004.
(ii) For airplane Models AT-802 and AT-802A, SNs beginning with
-0092, follow Drawing Number 20975, Sheet 2, Rev. A, dated September
1, 2004; and Process Specification 204, Rev. C, dated
November 16, 2004.
(2) The following presents the safe life and replacement times
as required in paragraph (h) of this AD:
Table 2--Safe Life and Replacement Times
----------------------------------------------------------------------------------------------------------------
SNs Wing spar lower cap safe life
----------------------------------------------------------------------------------------------------------------
AT-802-0001 through AT-802-0059............... 4,132 hours TIS.
AT-802-0060 through AT-802-0091............... 4,188 hours TIS.
All beginning with AT-802-0092................ 8,163 hours TIS.
AT-802A-0001 through AT-802A-0059............. 4,969 hours TIS.
AT-802A-0060 through AT-802A-0091............. 4,531 hours TIS.
All beginning with AT-802A-0092............... 8,648 hours TIS.
----------------------------------------------------------------------------------------------------------------
(i) After replacing the wing main spar lower caps and hardware,
installing the web splice plate, and cold working the fastener holes
by following Snow Engineering Co. Drawing Number 20975, Sheet 3,
dated January 6, 2005 (SNs -0001 through -0091); or Sheet 2, Rev. A,
dated September 1, 2004 (all SNs beginning with -0092); and Process
Specification 204, Rev. C, dated November 16, 2004, the new
safe life for the wing main spar lower caps is as follows:
Table 3--New Safe Life for Wing Main Spar Lower Caps
----------------------------------------------------------------------------------------------------------------
SNs Wing spar lower cap safe life
----------------------------------------------------------------------------------------------------------------
All beginning with AT-802-0001................ 8,163 hours TIS.
All beginning with AT-802A-0001............... 8,648 hours TIS.
----------------------------------------------------------------------------------------------------------------
(j) For Models AT-802 and AT-802A airplanes, SNs -0001 through
-0091, in lieu of replacing the wing main spar lower cap at the safe
life hours TIS listed in Table 2 in paragraph (h) of this AD, you
may extend the safe life of the wing main spar lower caps by doing
the following actions. Between 3,200 hours TIS and the safe life
hours TIS for your airplane currently listed in Table 2 of this AD,
do the following, unless already done:
(1) Modify the wing by installing P/N 20997-2 web plate and P/N
20985-1 and 20985-2 extended 8-bolt splice blocks following Snow
Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated September 28,
2004.
(2) Cold-work the outboard two fastener holes in both the left
and right hand lower spar caps at the center splice following Snow
Engineering Co. Service Letter 240, dated September 30,
2004.
(3) Do an eddy current inspection of the wing center splice
joint outboard two fastener holes in both the right and left wing
main spar lower caps for cracks at the time of modification
following 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.
(4) If, before the effective date of this AD, an airplane has
already been modified following paragraph (j)(1) of this AD but did
not receive cold working in the outboard two fastener holes in both
the left and right hand lower spar caps following paragraph (j)(2)
of this AD, do the following:
(i) Initially do an eddy current inspection within the next
2,400 hours TIS after the modification, using the procedure in
paragraph (j)(3) of this AD, and repetitively thereafter at
intervals not to exceed every 1,200 hours TIS until the wing spar
lower cap reaches 8,000-hour TIS safe life.
(ii) At any time after the modification, you may do the cold
working in the outboard two fastener holes in both the left and
right hand lower spar caps following paragraph (j)(2) of this AD to
terminate the repetitive eddy current inspections required in
paragraph (j)(4)(i) of this AD.
(5) If you have modified your airplane following paragraph
(j)(1) of this AD prior to 3,200 hours TIS, you must do the
following to reach the extended 8,000-hour TIS safe life:
(i) If you did not cold work in the outboard two fastener holes
in both the left and right hand lower spar caps following paragraph
(j)(2) of this AD, you must do the repetitive eddy current
inspections following paragraph (j)(4)(i) of this AD until you
accumulate 4,800 hours TIS after the modification on the wing spar
lower cap. Upon accumulation of 4,800 hours TIS after the
modification on the wing spar lower cap, do the repetitive eddy
current inspections at intervals not to exceed every 600 hours TIS
until you reach the extended safe life of 8,000-hour TIS.
(ii) If you did cold work the outboard two fastener holes in
both the left and right hand lower spar caps following paragraph
(j)(2) of this AD, upon accumulation of 4,800 hours TIS after the
modification on the wing spar lower cap do the repetitive eddy
current inspections at intervals not to exceed every 600 hours TIS
until you reach the 8,000-hour TIS safe life.
(6) For the initial and repetitive eddy current inspections
required in paragraphs (j)(3), (j)(4)(i), (j)(5)(i) and (j)(5)(ii)
of this AD, follow the instructions as specified in 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. For any cracks found, follow the instructions for
repair or replacement as specified in paragraph (g) of this AD.
(k) If any cracks are found as a result of any inspection
required in paragraphs (e)(2), (j)(3), (j)4)(i), (j)(5)(i), and
(j)(5)(ii) of this AD, report any cracks you find within 10 days
after the cracks are found or within 10 days after April 21, 2006
(the effective date of AD 2006-08-09), whichever occurs later.
(1) Include in your report the aircraft SN, aircraft hours TIS,
wing spar cap hours TIS, crack location and size, corrective action
taken, and a point of contact name and phone number. Send your
report to Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43),
10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone:
(210) 308-3365; facsimile: (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 part 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.
Alternative Methods of Compliance (AMOCs)
(m) The Manager, Fort Worth Airplane Certification Office, ASW-
150, FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14
[[Page 39247]]
CFR 39.19. Send information to ATTN: Andy McAnaul, Aerospace
Engineer, ASW-150, FAA San Antonio MIDO-43, 10100 Reunion Pl., Ste.
650, San Antonio, Texas 78216; telephone: (210) 308-3365; fax: (210)
308-3370. Before using any approved AMOC on any airplane to which
the AMOC applies, notify your appropriate principal inspector (PI)
in the FAA Flight Standards District Office (FSDO), or lacking a PI,
your local FSDO.
(n) AMOCs approved for AD 2006-08-09 are not approved for this
AD.
Related Information
(o) To get copies of the service information referenced 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. To view the AD
docket, go to U.S. Department of Transportation, Docket Operations,
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey
Avenue, SE., Washington, DC 20590, or on the Internet at https://www.regulations.gov.
Issued in Kansas City, Missouri, on July 31, 2009.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-18815 Filed 8-5-09; 8:45 am]
BILLING CODE 4910-13-P
