Airworthiness Directives; Short Brothers Model SD3-60 Airplanes, 50160-50164 [05-16750]
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50160
Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(2) AMOCs approved previously according
to AD 98–13–33 are not approved as AMOCs
with this AD.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
Related Information
(p) French airworthiness directive F–2004–
092, issued June 23, 2004, also addresses the
subject of this AD.
Material Incorporated by Reference
(q) You must use the service information
listed in Table 3 of this AD to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
TABLE 3.—MATERIAL INCORPORATED BY REFERENCE
Airbus service bulletin
Revision level
Date
A300–27–0188 .........................................................................................................................
A300–27–0188, including Appendix 01 and Reporting Sheet ................................................
A300–27–6036 .........................................................................................................................
A300–27–6036, including Appendix 01 and Reporting Sheet ................................................
A300–55–0044 .........................................................................................................................
A300–55–6023 .........................................................................................................................
A310–27–2082 .........................................................................................................................
A310–27–2082, including Appendix 01 and Reporting Sheet ................................................
A310–55–2026 .........................................................................................................................
2 .............................................
05 ...........................................
2 .............................................
08 ...........................................
Original ...................................
Original ...................................
2 .............................................
05 ...........................................
Original ...................................
October 1, 1997.
April 16, 2004.
October 1, 1997.
April 16, 2004.
October 22, 1996.
October 22, 1996.
October 1, 1997.
April 16, 2004.
October 22, 1996.
(1) The Director of the Federal Register
approves th incorporatin by reference of the
service information listed in Table 4 of this
AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
TABLE 4.—NEW MATERIAL INCORPORATED BY REFERENCE
Airbus service bulletin
Revision level
A300–27–0188, including Appendix 01 and Reporting Sheet ................................................
A300–27–6036, including Appendix 01 and Reporting Sheet ................................................
A310–27–2082, including Appendix 01 and Reporting Sheet ................................................
05 ...........................................
08 ...........................................
05 ...........................................
(2) On July 30, 1998 (63 FR 34580, June 25,
1998), the Director of the Federal Register
previously approved the incorporation by
Date
April 16, 2004.
April 16, 2004.
April 16, 2004.
reference of the service information listed in
Table 5 of this AD.
TABLE 5.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Airbus service bulletin
A300–27–0188
A300–27–6036
A300–55–0044
A300–55–6023
A310–27–2082
A310–55–2026
Revision level
.........................................................................................................................
.........................................................................................................................
.........................................................................................................................
.........................................................................................................................
.........................................................................................................................
.........................................................................................................................
(3) To get copies of the service information,
contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France. To
view the AD docket, go to the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC. To review copies of the service
information, go to the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/federalregister/cfr/ibr-locations.html.
2 .............................................
2 .............................................
Original ...................................
Original ...................................
2 .............................................
Original ...................................
Issued in Renton, Washington, on August
12, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–16749 Filed 8–25–05; 8:45 am]
BILLING CODE 4910–13–P
Date
October
October
October
October
October
October
1, 1997.
1, 1997.
22, 1996.
22, 1996.
1, 1997.
22, 1996.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22168; Directorate
Identifier 2005–NM–146–AD; Amendment
39–14234; AD 2005–17–13]
RIN 2120–AA64
Airworthiness Directives; Short
Brothers Model SD3–60 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations
Final rule; request for
comments.
ACTION:
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FAA’s Determination and Requirements
of This AD
SUPPLEMENTARY INFORMATION:
Discussion
The FAA is adopting a new
airworthiness directive (AD) for all
Short Brothers Model SD3–60 airplanes.
This AD requires an inspection of the
rudder for damage, an inspection of the
balance weight attachment for
discrepancies, an inspection of the
rudder horn spar and cleats for cracking
and corrosion, and corrective action if
necessary. This AD results from events
in which fatigue cracking was found on
the rudder horn spar. We are issuing
this AD to detect and correct cracking
and corrosion of the rudder horn spar,
which could lead to detachment of the
mass balance weight of the rudder. The
detachment of the mass balance weight
could jam or restrict the movement of
the rudder, which could result in
reduced controllability of the airplane.
Loss of a mass balance weight could
also damage other parts of the airplane,
which could result in reduced
controllability of the airplane, or could
result in an injury to a person or damage
to property on the ground.
DATES: Effective September 12, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 12, 2005.
We must receive comments on this
AD by October 25, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
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.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Short Brothers, Airworthiness
& Engineering Quality, P.O. Box 241,
Airport Road, Belfast BT3 9DZ,
Northern Ireland, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1175;
fax (425) 227–1149.
SUMMARY:
The Civil Aviation Authority (CAA),
which is the airworthiness authority for
the United Kingdom, notified us that an
unsafe condition may exist on all Short
Brothers Model SD3–60 airplanes. The
CAA advises that there have been
reports of fatigue cracking found on the
rudder horn spar. In one event, the
rudder horn spar failed and the lower
mass balance weights detached from the
rudder horn spar, which caused
structural damage to the rudder’s front
spar, rib 14, and outer skin. Cracking of
the rudder horn spar, if not corrected,
could lead to detachment of the mass
balance weight of the rudder. The
detachment of the mass balance weight
could jam or restrict the movement of
the rudder, which could result in
reduced controllability of the airplane.
Loss of a mass balance weight could
also damage other parts of the airplane,
which could result in reduced
controllability of the airplane, or could
result in an injury to a person or damage
to property on the ground.
Relevant Service Information
Short Brothers has issued Alert
Service Bulletin SD360–55–A22,
Revision 1, dated August 4, 2005. The
service bulletin describes procedures for
doing a visual inspection of the rudder
for damage and an inspection of the
balance weight attachment for
discrepancies (discrepancies include
potential rudder restriction and
detachment of the balance weight). The
service bulletin also describes
procedures for a detailed visual
inspection of the rudder horn spar for
cracking and corrosion, a borescope
inspection of the cleats for cracking and
corrosion, and corrective action if
necessary. The corrective action
includes replacement of the rudder horn
spar and cleats as specified in Part C of
the service bulletin and an optional
temporary repair to the rudder horn spar
that includes replacement of the cleats.
The CAA mandated the service
bulletin and issued British
airworthiness directive G–2005–0021,
dated July 6, 2005, to ensure the
continued airworthiness of these
airplanes in the United Kingdom.
The service bulletin refers to Short
Brothers Repair Drawing SD3–03–
6825XB, dated July 2005, as the
appropriate source of service
information for doing the temporary
repair to the rudder horn spar including
replacement of the cleats.
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50161
This airplane model is manufactured
in the United Kingdom and is type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, the CAA has
kept the FAA informed of the situation
described above. We have examined the
CAA’s findings, evaluated all pertinent
information, and determined that we
need to issue an AD for products of this
type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to
detect and correct cracking and
corrosion of the rudder horn spar,
which could lead to detachment of the
mass balance weight of the rudder. The
detachment of the mass balance weight
could jam or restrict the movement of
the rudder, which could result in
reduced controllability of the airplane.
Loss of a mass balance weight could
also damage other parts of the airplane,
which could result in reduced
controllability of the airplane, or could
result in an injury to a person or damage
to property on the ground. This AD
requires accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Differences Between
the AD and the Service Bulletin.’’
Differences Between the AD and the
Service Bulletin
When less than five cracks are
detected in the rudder horn spar that are
each 1 inch or less (and no cracks found
on the cleats), Shorts Alert Service
Bulletin SD360–55–A22 specifies to
repetitively inspect every 25 flight
cycles for up to 100 flight cycles.
However, this AD does not permit
further flight if any crack is detected in
the rudder horn spar. We have
determined that, because of the safety
implications and consequences
associated with that cracking, any crack
found on the rudder horn spar must be
repaired before further flight. In
addition, the service bulletin does not
specify what the corrective action is
after 100 flight cycles. This AD requires
either replacing the rudder horn spar
with a new rudder horn spar and
replacing the cleats, part number (P/N)
SD3–33–6404XA and –6405XA, with
new improved cleats; or doing the
temporary repair and then replacing the
rudder horn spar with a new rudder
horn spar.
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50162
Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations
Clarification of Inspection Terminology
In this AD, the ‘‘visual inspection’’
specified in the service bulletin is
referred to as a ‘‘general visual
inspection.’’ We have included the
definition for a general visual inspection
in a note in the AD.
In this AD, the ‘‘detailed visual
inspection’’ specified in the service
bulletin is referred to as a ‘‘detailed
inspection.’’ We have included the
definition for a detailed inspection in a
note in the AD.
Interim Action
We consider this AD interim action. If
final action is later identified, we may
consider further rulemaking.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD; therefore, providing notice and
opportunity for public comment before
the AD is issued is impracticable, and
good cause exists to make this AD
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to the address listed under
the ADDRESSES section. Include ‘‘Docket
No. FAA–2005–22168; Directorate
Identifier 2005–NM–146–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD that might suggest a need to
modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
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person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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 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 the 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
■
2005–17–13 Short Brothers PLC:
Amendment 39–14234. Docket No.
FAA–2005–22168; Directorate Identifier
2005–NM–146–AD.
Effective Date
(a) This AD becomes effective September
12, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Shorts Model
SD3–60 airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from events in which
fatigue cracking was found on the rudder
horn spar. The FAA is issuing this AD to
detect and correct cracking and corrosion of
the rudder horn spar, which could lead to
detachment of the mass balance weight of the
rudder. The detachment of the mass balance
weight could jam or restrict the movement of
the rudder, which could result in reduced
controllability of the airplane. Loss of a mass
balance weight could also damage other parts
of the airplane, which could result in
reduced controllability of the airplane, or
could result in an injury to a person or
damage to property on the ground.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Service Bulletin
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Shorts Alert Service Bulletin
SD360–55–A22, Revision 1, dated August 4,
2005.
Inspections
(g) Within 5 flight cycles after the effective
date of this AD, do a general visual
inspection of the rudder for damage and of
the balance weight attachment for
discrepancies in accordance with Part A of
the service bulletin.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
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Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
(1) If no damage and no discrepancy is
found, no further action is necessary for this
paragraph.
(2) If any damage or discrepancy is found,
before further flight, do a detailed inspection
of the rudder horn spar and a borescope
inspection of the cleats for cracking and
corrosion in accordance with Part B of the
service bulletin.
Note 2: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(h) At the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD, do a
detailed inspection of the rudder horn spar
and a borescope inspection of the cleats for
cracking and corrosion in accordance with
Part B of the service bulletin, unless the
inspections have already been done as
required by paragraph (g)(2) of this AD.
50163
(1) For airplanes on which a heavy landing
has occurred before the effective date of this
AD, do the inspections within 20 flight
cycles or 7 days after the effective date of this
AD, whichever occurs first.
(2) For airplanes on which a heavy landing
has not occurred before the effective date of
this AD, do the inspections at the earlier of
the times specified in paragraphs (h)(2)(i),
(h)(2)(ii), and (h)(2)(iii) of this AD.
(i) For airplanes on which a heavy landing
occurs after the effective date of this AD, do
the inspections within 20 flight cycles or 7
days after the heavy landing occurred,
whichever occurs first.
(ii) For airplanes that have accumulated
28,800 or more total flight hours, do the
inspections within 20 flight cycles or 7 days
after the effective date of this AD, whichever
occurs first.
(iii) At the applicable time specified in
Table 1 of this AD.
TABLE 1.—CERTAIN COMPLIANCE TIMES FOR PART B INSPECTIONS
For airplanes that—
Do the inspections—
Have accumulated 25,000 or less total flight cycles ................................
Within 80 flight cycles or 28 days after the effective date of this AD,
whichever occurs first.
Within 40 flight cycles or 14 days after the effective date of this AD,
whichever occurs first.
Within 20 flight cycles or 7 days after the effective date of this AD,
whichever occurs first.
Have accumulated more than 25,000 total flight cycles but less than
50,000 total flight cycles.
Have accumulated 50,000 or more total flight cycles ..............................
Corrective Actions
(i) If, during any inspection required by
paragraph (g)(2) or (h) of this AD, no crack
is found and any corrosion found is within
the limits specified in the service bulletin, no
further action is required by this paragraph.
(j) If any crack is found during any
inspection required by paragraph (g)(2) or (h)
of this AD, do the corrective action specified
in paragraph (j)(1), (j)(2), or (j)(3) of this AD,
as applicable, except as required by
paragraph (k) of this AD.
(1) If any crack is found on the rudder horn
spar and there is no crack on any of the
cleats, do the actions specified in paragraph
(j)(1)(i) or (j)(1)(ii) of this AD.
(i) Before further flight, replace the rudder
horn spar with a new rudder horn spar and
replace the cleats, part numbers (P/N) SD3–
33–6404XA and –6405XA, with new cleats,
in accordance with Part C of the service
bulletin.
(ii) Before further flight, do the temporary
repair in accordance with Short Brothers
Repair Drawing SD3–03–6825XB, dated July
2005, and within 300 flight cycles, replace
the rudder horn spar with a new rudder horn
spar, in accordance with Part C of the service
bulletin.
(2) If any crack is found on the rudder horn
spar and any crack is found on any cleat, do
the actions specified in paragraph (j)(2)(i) or
(j)(2)(ii) of this AD.
(i) Before further flight, replace the rudder
horn spar with a new rudder horn spar and
replace all three cleats with new cleats, in
accordance with Part C of the service
bulletin.
(ii) Before further flight, do the temporary
repair in accordance with Short Brothers
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Repair Drawing SD3–03–6825XB, dated July
2005, and within 300 flight cycles, replace
the rudder horn spar with a new rudder horn
spar, in accordance with Part C of the service
bulletin.
(3) If any crack is found on any of the
cleats and no cracks are found on the rudder
horn spar, before further flight, replace the
cleats with new cleats in accordance with
Part C of the service bulletin or in accordance
with Short Brothers Repair Drawing SD3–03–
6825XB, dated July 2005.
(k) If, during any inspection required by
paragraph (g)(2) or (h) of this AD, any
corrosion is found that is outside the limits
specified in the service bulletin, before
further flight, replace the corroded part with
a new part, in accordance with Part C of the
service bulletin.
Actions Accomplished in Accordance With
Previous Issue of Service Information
(l) Actions accomplished before the
effective date of this AD in accordance with
Shorts Alert Service Bulletin SD360–55–A22,
dated July 6, 2005; and Short Brothers Repair
Drawing SD3–03–6825XA, dated July 2005;
are considered acceptable for compliance
with the corresponding actions specified in
this AD.
Alternative Methods of Compliance
(AMOCs)
(m) The Manager, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
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Related Information
(n) British airworthiness directive G–2005–
0021, dated July 6, 2005, also addresses the
subject of this AD.
Material Incorporated by Reference
(o) You must use Shorts Alert Service
Bulletin SD360–55–A22, Revision 1, dated
August 4, 2005; and Short Brothers Repair
Drawing SD3–03–6825XB, dated July 2005;
as applicable, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Short Brothers, Airworthiness &
Engineering Quality, PO Box 241, Airport
Road, Belfast BT3 9DZ, Northern Ireland, for
a copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA).
For information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
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50164
Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations
Issued in Renton, Washington, on August
12, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–16750 Filed 8–25–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. Arrius 2F Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
Turbomeca S.A. Arrius 2F turboshaft
engines. This AD requires replacing
certain O-rings on the check valve
piston in the lubrication unit. This AD
results from a report of a forced landing
of a Eurocopter EC120B helicopter. We
are issuing this AD to prevent an
uncommanded in-flight shutdown of the
engine, which could result in a forced
autorotation landing and damage to the
helicopter.
DATES: Effective September 12, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of September 12, 2005.
We must receive any comments on
this AD by October 25, 2005.
ADDRESSES: Use one of the following
addresses to comment on this AD:
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
16:11 Aug 25, 2005
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–2599, telephone
(781) 238–7175; fax (781) 238–7199.
The
Direction General De L’Aviation Civile
(DGAC), which is the airworthiness
authority for France, recently notified us
that an unsafe condition might exist on
Turbomeca S.A. Arrius 2F turboshaft
engines. In addition, on May 13, 2005,
an uncommanded in-flight engine
shutdown (IFSD) of an Arrius 2F engine
resulted in the forced landing of a
Eurocopter EC120B helicopter in the
Gulf of Mexico. Investigation of the
engine found that an interruption of
engine lubrication due to excessive
swelling of the check valve O-ring in the
lubrication unit caused the IFSD. The
amount of swelling of the O-ring
depends on the class of oil used,
standard (STD) or high-thermal stability
(HTS), and the engine operating time.
This condition, if not corrected, could
result in an uncommanded in-flight
shutdown of the engine, which could
result in a forced autorotation landing
and damage to the helicopter.
SUPPLEMENTARY INFORMATION:
[Docket No. FAA–2005–22039; Directorate
Identifier 2005–NE–33–AD; Amendment 39–
14238; AD 2005–17–17]
VerDate Aug<18>2005
Contact Turbomeca S.A., 40220
Tarnos, France; telephone 33 05 59 74
40 00, fax 33 05 59 74 45 15, for the
service information identified in this
AD.
Jkt 205001
Relevant Service Information
We have reviewed and approved the
technical contents of Turbomeca Alert
Service Bulletin (ASB) No. A319 79
4802, dated June 21, 2005, that
describes procedures for replacing the
O-ring on the check valve piston of the
lubrication unit. The DGAC classified
this alert service bulletin as mandatory
and issued AD No. F–2005–122, dated
July 20, 2005, in order to ensure the
airworthiness of these Turbomeca S.A.
Arrius 2F turboshaft engines in France.
Bilateral Airworthiness Agreement
This turboshaft engine model is
manufactured in France, and is type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Under this bilateral
airworthiness agreement, the DGAC
kept the FAA informed of the situation
described above. We have examined the
findings of the DGAC, reviewed all
available information, and determined
that AD action is necessary for products
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
of this type design that are certificated
for operation in the United States.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other Turbomeca S.A. Arrius 2F
turboshaft engines of the same type
design. We are issuing this AD to
prevent an uncommanded in-flight
shutdown of the engine, which could
result in a forced autorotation landing
and damage to the helicopter. This AD
requires replacing the O-ring on the
check valve piston in the lubrication
unit at the following intervals:
• For engines that use HTS or an
unknown class oil, within 300 hours
time-since-new (TSN) or 50 hours after
the effective date of this AD, whichever
is later.
• For engines that use STD class oil,
within 450 hours TSN or 50 hours after
the effective date of this AD, whichever
is later.
• Thereafter, replace the O-ring
within 300 hours time-since-last
replacement (TSR) on engines that use
HTS class oil or 500 hours TSR on
engines that use STD class oil.
You must use the service information
described previously to perform the
actions required by this AD.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in less than 30
days.
Interim Action
These actions are interim actions and
we may take further rulemaking actions
in the future.
Comments Invited
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 send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2005–22039; Directorate Identifier
2005–NE–33–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
E:\FR\FM\26AUR1.SGM
26AUR1
]]>Agencies
[Federal Register Volume 70, Number 165 (Friday, August 26, 2005)]
[Rules and Regulations]
[Pages 50160-50164]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16750]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22168; Directorate Identifier 2005-NM-146-AD;
Amendment 39-14234; AD 2005-17-13]
RIN 2120-AA64
Airworthiness Directives; Short Brothers Model SD3-60 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 50161]]
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Short Brothers Model SD3-60 airplanes. This AD requires an inspection
of the rudder for damage, an inspection of the balance weight
attachment for discrepancies, an inspection of the rudder horn spar and
cleats for cracking and corrosion, and corrective action if necessary.
This AD results from events in which fatigue cracking was found on the
rudder horn spar. We are issuing this AD to detect and correct cracking
and corrosion of the rudder horn spar, which could lead to detachment
of the mass balance weight of the rudder. The detachment of the mass
balance weight could jam or restrict the movement of the rudder, which
could result in reduced controllability of the airplane. Loss of a mass
balance weight could also damage other parts of the airplane, which
could result in reduced controllability of the airplane, or could
result in an injury to a person or damage to property on the ground.
DATES: Effective September 12, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 12,
2005.
We must receive comments on this AD by October 25, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov 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.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Short Brothers, Airworthiness & Engineering Quality, P.O.
Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, notified us that an unsafe condition
may exist on all Short Brothers Model SD3-60 airplanes. The CAA advises
that there have been reports of fatigue cracking found on the rudder
horn spar. In one event, the rudder horn spar failed and the lower mass
balance weights detached from the rudder horn spar, which caused
structural damage to the rudder's front spar, rib 14, and outer skin.
Cracking of the rudder horn spar, if not corrected, could lead to
detachment of the mass balance weight of the rudder. The detachment of
the mass balance weight could jam or restrict the movement of the
rudder, which could result in reduced controllability of the airplane.
Loss of a mass balance weight could also damage other parts of the
airplane, which could result in reduced controllability of the
airplane, or could result in an injury to a person or damage to
property on the ground.
Relevant Service Information
Short Brothers has issued Alert Service Bulletin SD360-55-A22,
Revision 1, dated August 4, 2005. The service bulletin describes
procedures for doing a visual inspection of the rudder for damage and
an inspection of the balance weight attachment for discrepancies
(discrepancies include potential rudder restriction and detachment of
the balance weight). The service bulletin also describes procedures for
a detailed visual inspection of the rudder horn spar for cracking and
corrosion, a borescope inspection of the cleats for cracking and
corrosion, and corrective action if necessary. The corrective action
includes replacement of the rudder horn spar and cleats as specified in
Part C of the service bulletin and an optional temporary repair to the
rudder horn spar that includes replacement of the cleats.
The CAA mandated the service bulletin and issued British
airworthiness directive G-2005-0021, dated July 6, 2005, to ensure the
continued airworthiness of these airplanes in the United Kingdom.
The service bulletin refers to Short Brothers Repair Drawing SD3-
03-6825XB, dated July 2005, as the appropriate source of service
information for doing the temporary repair to the rudder horn spar
including replacement of the cleats.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. We have examined the CAA's
findings, evaluated all pertinent information, and determined that we
need to issue an AD for products of this type design that are
certificated for operation in the United States.
Therefore, we are issuing this AD to detect and correct cracking
and corrosion of the rudder horn spar, which could lead to detachment
of the mass balance weight of the rudder. The detachment of the mass
balance weight could jam or restrict the movement of the rudder, which
could result in reduced controllability of the airplane. Loss of a mass
balance weight could also damage other parts of the airplane, which
could result in reduced controllability of the airplane, or could
result in an injury to a person or damage to property on the ground.
This AD requires accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the AD and the Service Bulletin.''
Differences Between the AD and the Service Bulletin
When less than five cracks are detected in the rudder horn spar
that are each 1 inch or less (and no cracks found on the cleats),
Shorts Alert Service Bulletin SD360-55-A22 specifies to repetitively
inspect every 25 flight cycles for up to 100 flight cycles. However,
this AD does not permit further flight if any crack is detected in the
rudder horn spar. We have determined that, because of the safety
implications and consequences associated with that cracking, any crack
found on the rudder horn spar must be repaired before further flight.
In addition, the service bulletin does not specify what the corrective
action is after 100 flight cycles. This AD requires either replacing
the rudder horn spar with a new rudder horn spar and replacing the
cleats, part number (P/N) SD3-33-6404XA and -6405XA, with new improved
cleats; or doing the temporary repair and then replacing the rudder
horn spar with a new rudder horn spar.
[[Page 50162]]
Clarification of Inspection Terminology
In this AD, the ``visual inspection'' specified in the service
bulletin is referred to as a ``general visual inspection.'' We have
included the definition for a general visual inspection in a note in
the AD.
In this AD, the ``detailed visual inspection'' specified in the
service bulletin is referred to as a ``detailed inspection.'' We have
included the definition for a detailed inspection in a note in the AD.
Interim Action
We consider this AD interim action. If final action is later
identified, we may consider further rulemaking.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to the
address listed under the ADDRESSES section. Include ``Docket No. FAA-
2005-22168; Directorate Identifier 2005-NM-146-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the AD that
might suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 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 the 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-17-13 Short Brothers PLC: Amendment 39-14234. Docket No. FAA-
2005-22168; Directorate Identifier 2005-NM-146-AD.
Effective Date
(a) This AD becomes effective September 12, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Shorts Model SD3-60 airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from events in which fatigue cracking was
found on the rudder horn spar. The FAA is issuing this AD to detect
and correct cracking and corrosion of the rudder horn spar, which
could lead to detachment of the mass balance weight of the rudder.
The detachment of the mass balance weight could jam or restrict the
movement of the rudder, which could result in reduced
controllability of the airplane. Loss of a mass balance weight could
also damage other parts of the airplane, which could result in
reduced controllability of the airplane, or could result in an
injury to a person or damage to property on the ground.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Service Bulletin
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Shorts Alert Service Bulletin SD360-
55-A22, Revision 1, dated August 4, 2005.
Inspections
(g) Within 5 flight cycles after the effective date of this AD,
do a general visual inspection of the rudder for damage and of the
balance weight attachment for discrepancies in accordance with Part
A of the service bulletin.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual
[[Page 50163]]
examination of an interior or exterior area, installation, or
assembly to detect obvious damage, failure, or irregularity. This
level of inspection is made from within touching distance unless
otherwise specified. A mirror may be necessary to ensure visual
access to all surfaces in the inspection area. This level of
inspection is made under normally available lighting conditions such
as daylight, hangar lighting, flashlight, or droplight and may
require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.''
(1) If no damage and no discrepancy is found, no further action
is necessary for this paragraph.
(2) If any damage or discrepancy is found, before further
flight, do a detailed inspection of the rudder horn spar and a
borescope inspection of the cleats for cracking and corrosion in
accordance with Part B of the service bulletin.
Note 2: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(h) At the applicable time specified in paragraph (h)(1) or
(h)(2) of this AD, do a detailed inspection of the rudder horn spar
and a borescope inspection of the cleats for cracking and corrosion
in accordance with Part B of the service bulletin, unless the
inspections have already been done as required by paragraph (g)(2)
of this AD.
(1) For airplanes on which a heavy landing has occurred before
the effective date of this AD, do the inspections within 20 flight
cycles or 7 days after the effective date of this AD, whichever
occurs first.
(2) For airplanes on which a heavy landing has not occurred
before the effective date of this AD, do the inspections at the
earlier of the times specified in paragraphs (h)(2)(i), (h)(2)(ii),
and (h)(2)(iii) of this AD.
(i) For airplanes on which a heavy landing occurs after the
effective date of this AD, do the inspections within 20 flight
cycles or 7 days after the heavy landing occurred, whichever occurs
first.
(ii) For airplanes that have accumulated 28,800 or more total
flight hours, do the inspections within 20 flight cycles or 7 days
after the effective date of this AD, whichever occurs first.
(iii) At the applicable time specified in Table 1 of this AD.
Table 1.--Certain Compliance Times for Part B Inspections
------------------------------------------------------------------------
For airplanes that-- Do the inspections--
------------------------------------------------------------------------
Have accumulated 25,000 or less total Within 80 flight cycles or 28
flight cycles. days after the effective date
of this AD, whichever occurs
first.
Have accumulated more than 25,000 total Within 40 flight cycles or 14
flight cycles but less than 50,000 days after the effective date
total flight cycles. of this AD, whichever occurs
first.
Have accumulated 50,000 or more total Within 20 flight cycles or 7
flight cycles. days after the effective date
of this AD, whichever occurs
first.
------------------------------------------------------------------------
Corrective Actions
(i) If, during any inspection required by paragraph (g)(2) or
(h) of this AD, no crack is found and any corrosion found is within
the limits specified in the service bulletin, no further action is
required by this paragraph.
(j) If any crack is found during any inspection required by
paragraph (g)(2) or (h) of this AD, do the corrective action
specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, as
applicable, except as required by paragraph (k) of this AD.
(1) If any crack is found on the rudder horn spar and there is
no crack on any of the cleats, do the actions specified in paragraph
(j)(1)(i) or (j)(1)(ii) of this AD.
(i) Before further flight, replace the rudder horn spar with a
new rudder horn spar and replace the cleats, part numbers (P/N) SD3-
33-6404XA and -6405XA, with new cleats, in accordance with Part C of
the service bulletin.
(ii) Before further flight, do the temporary repair in
accordance with Short Brothers Repair Drawing SD3-03-6825XB, dated
July 2005, and within 300 flight cycles, replace the rudder horn
spar with a new rudder horn spar, in accordance with Part C of the
service bulletin.
(2) If any crack is found on the rudder horn spar and any crack
is found on any cleat, do the actions specified in paragraph
(j)(2)(i) or (j)(2)(ii) of this AD.
(i) Before further flight, replace the rudder horn spar with a
new rudder horn spar and replace all three cleats with new cleats,
in accordance with Part C of the service bulletin.
(ii) Before further flight, do the temporary repair in
accordance with Short Brothers Repair Drawing SD3-03-6825XB, dated
July 2005, and within 300 flight cycles, replace the rudder horn
spar with a new rudder horn spar, in accordance with Part C of the
service bulletin.
(3) If any crack is found on any of the cleats and no cracks are
found on the rudder horn spar, before further flight, replace the
cleats with new cleats in accordance with Part C of the service
bulletin or in accordance with Short Brothers Repair Drawing SD3-03-
6825XB, dated July 2005.
(k) If, during any inspection required by paragraph (g)(2) or
(h) of this AD, any corrosion is found that is outside the limits
specified in the service bulletin, before further flight, replace
the corroded part with a new part, in accordance with Part C of the
service bulletin.
Actions Accomplished in Accordance With Previous Issue of Service
Information
(l) Actions accomplished before the effective date of this AD in
accordance with Shorts Alert Service Bulletin SD360-55-A22, dated
July 6, 2005; and Short Brothers Repair Drawing SD3-03-6825XA, dated
July 2005; are considered acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(m) The Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate, has the authority to approve AMOCs for this
AD, if requested in accordance with the procedures found in 14 CFR
39.19.
Related Information
(n) British airworthiness directive G-2005-0021, dated July 6,
2005, also addresses the subject of this AD.
Material Incorporated by Reference
(o) You must use Shorts Alert Service Bulletin SD360-55-A22,
Revision 1, dated August 4, 2005; and Short Brothers Repair Drawing
SD3-03-6825XB, dated July 2005; as applicable, to perform the
actions that are required by this AD, unless the AD specifies
otherwise. The Director of the Federal Register approved the
incorporation by reference of this document in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. Contact Short Brothers,
Airworthiness & Engineering Quality, PO Box 241, Airport Road,
Belfast BT3 9DZ, Northern Ireland, for a copy of this service
information. You may review copies at the Docket Management
Facility, U.S. Department of Transportation, 400 Seventh Street,
SW., Room PL-401, Nassif Building, Washington, DC; on the Internet
at https://dms.dot.gov; or at the National Archives and Records
Administration (NARA).
For information on the availability of this material at the
NARA, call (202) 741-6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.
[[Page 50164]]
Issued in Renton, Washington, on August 12, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-16750 Filed 8-25-05; 8:45 am]
BILLING CODE 4910-13-P
