Airworthiness Directives; Air Tractor, Inc. Models AT-802 and AT-802A Airplanes, 35616-35619 [2010-14990]
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Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations
Issued in Renton, Washington, on June 10,
2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–14979 Filed 6–22–10; 8:45 am]
BILLING CODE 4910–13–P
the safe life limit. 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.
This AD becomes effective on
July 28, 2010.
As of April 21, 2006 (71 FR 19994,
April 19, 2006) the Director of the
Federal Register approved the
incorporation by reference of 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. Process Specification
#204, Rev. C, dated November 16, 2004;
Snow Engineering Co. Service Letter
#215, page 5, titled ‘‘802 Spar Inspection
Holes and Vent Tube Mod,’’ dated
November 19, 2003; Snow Engineering
Co. Service Letter #240, dated
September 30, 2004; Snow Engineering
Co. Drawing Number 20975, Sheet 2,
Rev. A, dated September 1, 2004; Snow
Engineering Co. Drawing Number
20975, Sheet 3, dated January 6, 2005;
and Snow Engineering Co. Drawing
20995, Sheet 2, Rev. C, dated September
28, 2004, listed in this AD.
ADDRESSES: 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.
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. The docket
number is FAA–2009–0707; Directorate
Identifier 2009–CE–035–AD.
FOR FURTHER INFORMATION CONTACT:
Andy McAnaul, Aerospace Engineer,
DATES:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0707; Directorate
Identifier 2009–CE–035–AD; Amendment
39–16339; AD 2010–13–08]
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: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) to
supersede 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 serial
numbers (SNs) of the Models AT–802
and AT–802A airplanes affected by that
AD. Additionally, we are adding an
option of modifying the wing main spar
lower caps to extend the safe life limit
on the affected airplanes. Consequently,
this AD would keep the actions of AD
2006–08–09, clarify the affected SNs,
and add a modification option to extend
10100 Reunion Pl., Ste. 650, San
Antonio, Texas 78216; telephone: (210)
308–3365; fax: (210) 308–3370.
SUPPLEMENTARY INFORMATION:
Discussion
On July 31, 2009, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to all
Air Tractor Models AT–802 and AT–
802A airplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on August 6, 2009 (74 FR 39243). The
NPRM proposed to supersede AD 2006–
08–09 to clarify the SNs of the Models
AT–802 and AT–802A airplanes
affected by that AD. Additionally, we
proposed to add an option of modifying
the wing main spar lower caps to extend
the safe life limit on the affected
airplanes.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 187
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
Labor cost
Parts cost
Total cost per airplane
Total cost on U.S. operators
$500 to $800 ......................................
Not applicable .....................................
$500 to $800
$93,500 to $149,600
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We estimate the following costs to do
any necessary repairs for two spars that
may be required based on the results of
the inspection or the modification as an
option. We have no 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 .............................................................................................................
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$7,500
Total cost
(two spars)
per airplane
$25,500
Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations
We estimate the following costs to do
any necessary spar cap replacement
(two spars) that would be required
based on the results of the inspection.
We have no way of determining the
number of airplanes that may need this
replacement:
Parts cost
(two spars)
Labor cost (two spars)
495 work-hours × $80 per hour = $39,600 .............................................................................................................
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 AD.
Regulatory Findings
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We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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We prepared a summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2009–0707;
Directorate Identifier 2009–CE–035–AD’’
in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
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:
■
2010–13–08 Air Tractor, Inc.: Amendment
39–16339; Docket No. FAA–2009–0707;
Directorate Identifier 2009–CE–035–AD.
Effective Date
(a) This AD becomes effective on July 28,
2010.
Affected ADs
(b) This AD supersedes AD 2006–08–09,
Amendment 39–14565.
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35617
$39,100
Total cost
(two spars)
per airplane
$78,700
Applicability
(c) This AD affects Models 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 SNs of the Models
AT–802 and AT–802A airplanes affected by
AD 2006–08–09. 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.
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Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations
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.
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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:
(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 Models AT–802 and AT–802A
airplanes, SNs –0001 through –0091, follow
Drawing Number 20975, Sheet 3, dated
January 6, 2005; and Snow Engineering Co.
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Process Specification #204, Rev. C, dated
November 16, 2004.
(ii) For Models AT–802 and AT–802A
airplanes, SNs beginning with –0092, follow
Snow Engineering Co. Drawing Number
20975, Sheet 2, Rev. A, dated September 1,
2004; and Snow Engineering Co. 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
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.
Wing spar lower
cap safe life
4,132 hours TIS.
4,188 hours TIS.
8,163 hours TIS.
4,969 hours TIS.
4,531 hours TIS.
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 Snow Engineering Co. Drawing Number
20975, Sheet 2, Rev. A, dated September 1,
2004 (all SNs beginning with –0092); and
Snow Engineering Co. 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
All beginning with AT–
802–0001.
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Wing spar lower
cap safe life
8,163 hours TIS.
Sfmt 4700
850 hours TIS.
1,700 hours
TIS.
TABLE 3—NEW SAFE LIFE FOR WING
MAIN SPAR LOWER CAPS—Continued
SNs
All beginning with AT–
802A–0001.
Wing spar lower
cap safe life
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 July 28, 2010 (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
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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 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 Andy 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.
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(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
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: https://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.
Material Incorporated by Reference
(p) You must use 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. Process
Specification #204, Rev. C, dated November
16, 2004; Snow Engineering Co. Service
Letter #215, page 5, titled ‘‘802 Spar
Inspection Holes and Vent Tube Mod,’’ dated
November 19, 2003; Snow Engineering Co.
Service Letter #240, dated September 30,
2004; Snow Engineering Co. Drawing
Number 20975, Sheet 2, Rev. A, dated
September 1, 2004; Snow Engineering Co.
Drawing Number 20975, Sheet 3, dated
January 6, 2005; and Snow Engineering Co.
Drawing 20995, Sheet 2, Rev. C, dated
September 28, 2004, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) On April 21, 2006 (71 FR 19994, April
19, 2006), the Director of the Federal Register
approved the incorporation by reference of
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.
Process Specification #204, Rev. C, dated
November 16, 2004; Snow Engineering Co.
Service Letter #215, page 5, titled ‘‘802 Spar
Inspection Holes and Vent Tube Mod,’’ dated
November 19, 2003; Snow Engineering Co.
Service Letter #240, dated September 30,
2004; Snow Engineering Co. Drawing
Number 20975, Sheet 2, Rev. A, dated
September 1, 2004; Snow Engineering Co.
Drawing Number 20975, Sheet 3, dated
January 6, 2005; and Snow Engineering Co.
Drawing 20995, Sheet 2, Rev. C, dated
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35619
September 28, 2004, under 5 U.S.C. 552(a)
and 1 CFR part 51.
(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: https://
www.airtractor.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, 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 June 15,
2010.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–14990 Filed 6–22–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0122; Directorate
Identifier 2009–CE–067–AD; Amendment
39–16338; AD 2010–13–07]
RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Models PA–32R–301T and
PA–46–350P Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Piper Aircraft, Inc. Models PA–32R–
301T and PA–46–350P airplanes. This
AD requires you to replace any spotwelded, V-band exhaust coupling with
a riveted, V-band exhaust coupling. This
AD results from reports that spotwelded, V-band exhaust couplings are
failing. We are issuing this AD to
prevent failure of the V-band exhaust
coupling, which could cause the
exhaust pipe to detach from the
turbocharger. This failure could result
in release of high-temperature gases
inside the engine compartment and
possibly cause an in-flight fire. An inflight fire could lead to loss of control.
DATES: This AD becomes effective on
July 28, 2010.
E:\FR\FM\23JNR1.SGM
23JNR1
]]>Agencies
[Federal Register Volume 75, Number 120 (Wednesday, June 23, 2010)]
[Rules and Regulations]
[Pages 35616-35619]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-14990]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0707; Directorate Identifier 2009-CE-035-AD;
Amendment 39-16339; AD 2010-13-08]
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: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) to
supersede 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 serial numbers (SNs) of the Models AT-802 and AT-
802A airplanes affected by that AD. Additionally, we are adding an
option of modifying the wing main spar lower caps to extend the safe
life limit on the affected airplanes. Consequently, this AD would keep
the actions of AD 2006-08-09, clarify the affected SNs, and add a
modification option to extend the safe life limit. 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 becomes effective on July 28, 2010.
As of April 21, 2006 (71 FR 19994, April 19, 2006) the Director of
the Federal Register approved the incorporation by reference of 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. Process Specification
204, Rev. C, dated November 16, 2004; Snow Engineering Co.
Service Letter 215, page 5, titled ``802 Spar Inspection Holes
and Vent Tube Mod,'' dated November 19, 2003; Snow Engineering Co.
Service Letter 240, dated September 30, 2004; Snow Engineering
Co. Drawing Number 20975, Sheet 2, Rev. A, dated September 1, 2004;
Snow Engineering Co. Drawing Number 20975, Sheet 3, dated January 6,
2005; and Snow Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated
September 28, 2004, listed in this AD.
ADDRESSES: 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.
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. The docket number is FAA-2009-0707;
Directorate Identifier 2009-CE-035-AD.
FOR FURTHER INFORMATION CONTACT: Andy McAnaul, Aerospace Engineer,
10100 Reunion Pl., Ste. 650, San Antonio, Texas 78216; telephone: (210)
308-3365; fax: (210) 308-3370.
SUPPLEMENTARY INFORMATION:
Discussion
On July 31, 2009, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to all Air Tractor Models AT-802 and AT-802A airplanes.
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on August 6, 2009 (74 FR 39243). The NPRM
proposed to supersede AD 2006-08-09 to clarify the SNs of the Models
AT-802 and AT-802A airplanes affected by that AD. Additionally, we
proposed to add an option of modifying the wing main spar lower caps to
extend the safe life limit on the affected airplanes.
Comments
We provided the public the opportunity to participate in developing
this AD. We received no comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 187 airplanes in the U.S.
registry.
We estimate the following costs to do the inspection:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane Total cost on U.S. 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 inspection
or the modification as an option. We have no way of determining the
number of airplanes that may need this repair:
------------------------------------------------------------------------
Total cost
Labor cost (two spars) Parts cost (two spars)
(two spars) per airplane
------------------------------------------------------------------------
225 work-hours x $80 per hour = $18,000. $7,500 $25,500
------------------------------------------------------------------------
[[Page 35617]]
We estimate the following costs to do any necessary spar cap
replacement (two spars) that would be required based on the results of
the inspection. We have no way of determining the number of airplanes
that may need this replacement:
------------------------------------------------------------------------
Total cost
Labor cost (two spars) Parts 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 AD.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2009-0707; Directorate Identifier 2009-CE-035-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2006-08-09, amendment 39-14565 (71 FR 27784, May 12, 2006), and adding
the following new AD:
2010-13-08 Air Tractor, Inc.: Amendment 39-16339; Docket No. FAA-
2009-0707; Directorate Identifier 2009-CE-035-AD.
Effective Date
(a) This AD becomes effective on July 28, 2010.
Affected ADs
(b) This AD supersedes AD 2006-08-09, Amendment 39-14565.
Applicability
(c) This AD affects Models 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 SNs of the Models AT-802 and AT-802A airplanes affected
by AD 2006-08-09. 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.
[[Page 35618]]
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 1,700 hours TIS 850 hours TIS.
0001 through -0091. 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 -0091. cold[dash]worked cold[dash]working procedure in
fastener holes Service Letter 244,
following Service dated April 25, 2005, it includes
Letter 244, dated April inspection.
25, 2005.
----------------------------------------------------------------------------------------------------------------
(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 Models AT-802 and AT-802A airplanes, SNs -0001 through -
0091, follow Drawing Number 20975, Sheet 3, dated January 6, 2005;
and Snow Engineering Co. Process Specification 204, Rev. C,
dated November 16, 2004.
(ii) For Models AT-802 and AT-802A airplanes, SNs beginning with
-0092, follow Snow Engineering Co. Drawing Number 20975, Sheet 2,
Rev. A, dated September 1, 2004; and Snow Engineering Co. 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 Snow Engineering
Co. Drawing Number 20975, Sheet 2, Rev. A, dated September 1, 2004
(all SNs beginning with -0092); and Snow Engineering Co. 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 July 28, 2010 (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
[[Page 35619]]
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 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 Andy 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 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: https://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.
Material Incorporated by Reference
(p) You must use 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. Process Specification 204, Rev. C, dated November 16,
2004; Snow Engineering Co. Service Letter 215, page 5,
titled ``802 Spar Inspection Holes and Vent Tube Mod,'' dated
November 19, 2003; Snow Engineering Co. Service Letter 240,
dated September 30, 2004; Snow Engineering Co. Drawing Number 20975,
Sheet 2, Rev. A, dated September 1, 2004; Snow Engineering Co.
Drawing Number 20975, Sheet 3, dated January 6, 2005; and Snow
Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated September 28,
2004, to do the actions required by this AD, unless the AD specifies
otherwise.
(1) On April 21, 2006 (71 FR 19994, April 19, 2006), the
Director of the Federal Register approved the incorporation by
reference of 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. Process Specification 204, Rev. C, dated November 16,
2004; Snow Engineering Co. Service Letter 215, page 5,
titled ``802 Spar Inspection Holes and Vent Tube Mod,'' dated
November 19, 2003; Snow Engineering Co. Service Letter 240,
dated September 30, 2004; Snow Engineering Co. Drawing Number 20975,
Sheet 2, Rev. A, dated September 1, 2004; Snow Engineering Co.
Drawing Number 20975, Sheet 3, dated January 6, 2005; and Snow
Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated September 28,
2004, under 5 U.S.C. 552(a) and 1 CFR part 51.
(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: https://www.airtractor.com.
(3) You may review copies of the service information
incorporated by reference for this AD at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the
Central Region, call (816) 329-3768.
(4) You may also review copies of the service information
incorporated by reference for this AD at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, 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 June 15, 2010.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-14990 Filed 6-22-10; 8:45 am]
BILLING CODE 4910-13-P
