[Federal Register: June 21, 2005 (Volume 70, Number 118)]
[Rules and Regulations]
[Page 35519-35523]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21jn05-5]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-24163; Directorate Identifier 2005-CE-30-AD;
Amendment 39-14144; AD 2005-12-51]
RIN 2120-AA64
Airworthiness Directives; Rockwell International (Aircraft
Specification No. A-2-575 previously held by North American and
recently purchased by Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-
6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G
Airplanes; and Autair Ltd. (Aircraft Specification No. AR-11 previously
held by Noorduyn Aviation Ltd.) Model Harvard (Army AT-16) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rockwell International (Aircraft Specification No. A-2-575 previously
held by North American and recently purchased by Boeing) Models AT-6
(SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F
(SNJ-6), BC-1A, SNJ-7, and T-6G airplanes; and Autair Ltd. (Aircraft
Specification No. AR-11 previously held by Noorduyn Aviation Ltd.)
Model Harvard (Army AT-16) airplanes. This AD contains the same
information as emergency AD 2005-12-51 and publishes the action in the
Federal Register. It requires immediate and repetitive inspections of
the inboard and outboard, upper and lower wing attach angles (except
for the nose angles) of both wings for fatigue cracks; and, if any
crack is found, replacement of the cracked angle with a new angle. This
AD is the result of a report of a Rockwell International Model SNJ-6
(AT-6F) airplane crash that occurred on May 9, 2005, resulting in two
fatalities. We are issuing this AD to detect and correct any fatigue
crack in the inboard and outboard, upper and lower wing attach angles
(except for the nose angles) of either wing, which could result in
failure of the wing. This failure could lead to loss of control of the
aircraft.
DATES: This AD becomes effective on June 23, 2005, to all affected
persons who did not receive emergency AD 2005-12-51, issued June 8,
2005. Emergency AD 2005-12-51 contained the requirements of this
amendment and
[[Page 35520]]
became effective immediately upon receipt.
We must receive any comments on this AD by August 15, 2005.
ADDRESSES: Use one of the following to submit comments on this AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-001.
Fax: 1-202-493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
The type certificate holders have not issued any service
information that addresses this safety issue.
To view the comments to this AD, go to http://dms.dot.gov. The
docket number is FAA-2005-24163; Directorate Identifier 2005-CE-30-AD.
FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aerospace Engineer, FAA,
Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; telephone:
(562) 627-5232; facsimile: (562) 627-5210; e-mail: fred.guerin@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
What events caused previous FAA AD action? The FAA has received a
report of a Rockwell International Model SNJ-6 (AT-6F) airplane crash
that occurred on May 9, 2005, resulting in two fatalities. The
investigation revealed a large fatigue crack in the failed lower
inboard wing attach angle. The aircraft was used for hire in aerobatic
training.
On June 8, 2005, we issued emergency AD 2005-12-51 to require
immediate and repetitive inspections of the inboard and outboard, upper
and lower wing attach angles (except for the nose angles) of both wings
for fatigue cracks; and, if any crack is found, replacement of the
cracked angle with a new angle.
Why is it important to publish this AD? The FAA found that
immediate corrective action was required, that notice and opportunity
for prior public comment were impracticable and contrary to the public
interest, and that good cause existed to make the AD effective
immediately by individual letters issued on June 8, 2005, to all known
U.S. operators of Rockwell International (Aircraft Specification No. A-
2-575 previously held by North American and recently purchased by
Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D
(SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G airplanes; and Autair
Ltd. (Aircraft Specification No. AR-11 previously held by Noorduyn
Aviation Ltd.) Model Harvard (Army AT-16) airplanes. These conditions
still exist, and the AD is published in the Federal Register as an
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR
39.13) to make it effective to all persons.
Will FAA take future rulemaking action on this subject? The
National Transportation Safety Board (NTSB) is still investigating the
accident. When all information from the investigation becomes
available, FAA may take additional AD action to address continued
operational safety of the affected airplanes. This could include, but
is not limited to, inspections, modifications, and/or replacement of
critical components.
Comments Invited
Will I have the opportunity to comment before you issue the rule?
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-24163;
Directorate Identifier 2005-CE-30-AD'' in the subject line of your
comments. If you want us to acknowledge receipt of your mailed
comments, send us a self-addressed, stamped postcard with the docket
number written on it; we will date-stamp your postcard and mail it back
to you. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it. If a person contacts us through a
nonwritten communication, and that contact relates to a substantive
part of this AD, we will summarize the contact and place the summary in
the docket. We will consider all comments received by the closing date
and may amend the AD in light of those comments.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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
Will this AD impact various entities? We have determined that this
AD will not have federalism implications under Executive Order 13132.
This AD will not have a substantial direct effect on the States, on the
relationship between the national government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
Will this AD involve a significant rule or regulatory action? For
the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD (and
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-2005-24163; Directorate Identifier 2005-CE-30-AD'' in your
request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
[[Page 35521]]
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding a new AD to read as follows:
2005-12-51 Rockwell International (Aircraft Specification No. A-2-
575 previously held by North American and recently purchased by
Boeing) and Autair Ltd. (Aircraft Specification No. AR-11 previously
held by Noorduyn Aviation Ltd.): Amendment 39-14144; Docket No. FAA-
2005-24163; Directorate Identifier 2005-CE-30-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on June 23, 2005, to all affected
persons who did not receive emergency AD 2005-12-51, issued June 8,
2005. Emergency AD 2005-12-51 contained the requirements of this
amendment and became effective immediately upon receipt.
Are Any Other ADs Affected By This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B,
AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard (Army
AT-16), SNJ-7, and T-6G airplanes, all serial numbers, that are
certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of a report of a Rockwell
International Model SNJ-6 (AT-6F) airplane crash that occurred on
May 9, 2005, resulting in two fatalities. We are issuing this AD to
detect and correct cracking in the wing spars before the cracks grow
to failure. Such a wing failure could result in the wing separating
from the airplane with consequent loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Perform a fluorescent (i) Initially Follow the Appendix
penetrant inspection of all inspect before to this AD.
inboard and outboard, upper further flight
and lower wing attach after June 23, 2005
angles (except for the nose (the effective date
angles) ofboth wings for of this AD), unless
cracks. Replace the angles previously done
as necessary. within the last 10
hours time-in-
service (TIS),
except for those
who received
emergency AD 2005-
12-51, issued June
8, 2005. Emergency
AD 2005-12-51
contained the
requirements of
this amendment and
became effective
immediately upon
receipt.
(ii) Repetitively
inspect thereafter
every 200 hours TIS.
(iii) Replace angles
as necessary prior
to further flight
after the
inspection where
cracks are found.
-----------------------------
(2) For all airplanes: Within 7 days after Send the form
Report to FAA the results the inspection (Figure 1 of this
of the initial inspection required by AD) to FAA, Los
required by paragraph paragraph (e)(1) of Angeles ACO, 3960
(e)(1) of this AD even if this AD or within 7 Paramount Blvd.,
no damage is found and even days after June 23, Lakewood, CA 90712;
if the inspection was 2005 (the effective facsimile: (562)
previously done. The Office date of this AD), 627-5210. E-mail:
of Management andBudget except that this fred.guerin@faa.gov
(OMB) approved the action was already .
information collection required upon
requirements contained in receipt for those
this regulation under the who received
provisions of the Paperwork emergency AD 2005-
Reduction Act of 1980 (44 12-51.Therefore,
U.S.C. 3501 and those those who sent in a
following sections) and report through
assigned OMB Control Number emergency AD 2005-
2120-0056. 12-51 do not have
to resend that
initial report.
-----------------------------
(3) You may operate the You may operate the Not Applicable.
airplane to return/position airplane up to 10
the airplane to a home hours TIS provided
base, hangar, maintenance the flight(s)
facility, etc., for the occur(s) no later
purpose of doing the than 30 days after
inspection required by this June 8, 2005. This
AD provided you follow the is a one-time
limitations in paragraph provision.
(f) of this AD.
-----------------------------
(4) Special flight permits Use the procedures Not Applicable.
are allowed for this AD. in 14 CFR part 39
See paragraph (f) of this and the
AD for restrictions. restrictions in
paragraph (f) of
this AD.
------------------------------------------------------------------------
BILLING CODE 4910-13-P
[[Page 35522]]
[GRAPHIC] [TIFF OMITTED] TR21JN05.004
BILLING CODE 4910-13-C
[[Page 35523]]
What Are the Flight Restrictions Specified in Paragraphs (e)(3) and
(e)(4) of This AD?
(f) During the time allowed before compliance with the initial
inspection required by paragraph (e)(1) of this AD, or for any
approved special flight permit, you must adhere to the following
limitations:
(1) Acrobatic maneuvers are prohibited.
(2) Flight into known or forecast moderate or severe turbulence
is prohibited.
(3) Day visual flight rules (VFR) operation only.
(4) Single pilot operation only (Passengers prohibited).
May I Request an Alternative Method of Compliance?
(g) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Los Angeles Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance or for further
information about this AD, contact Fred Guerin, Aerospace Engineer,
FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712;
telephone: (562) 627-5232; facsimile: (562) 627-5210; e-mail:
fred.guerin@faa.gov.
Where Do I View the AD Docket?
(h) To view the AD docket, go to the Docket Management Facility;
U.S. Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC 20590-001 or on the Internet
at http://dms.dot.gov. The docket number is FAA-2005-24163.
Issued in Kansas City, Missouri, on June 14, 2005.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
Appendix to AD 2005-12-51
Wing Attachment Angle Inspection for: Models AT-6 (SNJ-2), AT-6A (SNJ-
3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard
(Army AT-16), SNJ-7, and T-6G Airplanes
Procedures:
(1) Remove all outboard wing attach angle covers.
(2) Support outboard wing on appropriate stands to relieve the
weight on the wing attach bolts.
(3) On the upper wing attach angles, except for the forward and
aft five bolts on the angle, remove all of the through bolts that
attach the outboard wing (Do not remove bolts in the nose angle).
(4) Remove all paint down to the bare metal using solvent on
outer surface of affected angles. Do not sand or use media blasting
or use any method that would cover up or contaminate a crack. This
means not using Scotchbrite or a similar abrasive, which can
contaminate a crack for penetrant inspection.
(5) Use the penetrant manufacturer's cleaner, acetone, or 90-
percent or more alcohol solution to do a final surface cleaning
preparation step before the fluorescent penetrant inspection.
(6) Perform an inspection of the outboard and inboard wing
attach angles using a high sensitivity fluorescent dye penetrant
inspection procedure per the penetrant manufacturer's instructions.
Pay particular attention to cracks that may be present in the edge
of the spot faces closest to the radius of the angle. Also pay
attention to any small cracks that may be emanating from the edge of
the fasteners in any row of installed fasteners. Choose a
commercially available fluorescent inspection method that requires
the use of an ultraviolet (black light) in a darkened environment.
Do not use dye penetrant, which is read under normal lighting
conditions.
(7) Check the wing attachment angle for condition and for
security of rivets and bolts.
(8) If no cracks or major defects are found, replace nuts and
bolts following directions in paragraphs (11) and (12) of this
appendix of this AD, clean angle, and apply a corrosion protectant
coating paint (Alodine alone is not acceptable).
(9) On the upper wing, remove the forward and aft five bolts
that were previously left in place, and inspect the remaining
uninspected portion of the angles following the above procedure.
(10) On the lower wings, repeat the inspection on the bottom two
attach angles in the same sequence as on the top angles.
(11) When replacing bolts in angles, use only nuts, bolts, and
torque values as specified in ``Erection and Maintenance No. AN01-
60FFA-2'' or ``Erection and Maintenance No. AN01-60F-2'' as
applicable to the aircraft model. Bolts may be reused if upon
inspection they are found to be in airworthy condition. Nuts may be
reused as long as the nylon-locking feature is functional, and they
cannot be turned onto the bolt with fingers. Torque values for \1/
4\-inch bolts are 60-65 inch/lb, and for \5/16\-inch bolts are 100-
105 inch/lb. These torque values supersede those in the manuals.
(12) To assure that the nuts do not contact the shoulder of the
wing attach bolts and cause an under torque condition, assure that
no more than two threads are protruding from nut after torquing. If
more than two threads are protruding, replace with a bolt of the
correct length.
(13) If any cracks are found, replace the angle with a new part.
Send all cracked angles to Fred Guerin, Aerospace Engineer, FAA, Los
Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712.
[FR Doc. 05-12151 Filed 6-20-05; 8:45 am]
BILLING CODE 4910-13-P