Airworthiness Directives; Short Brothers Model SD3-60 SHERPA, SD3-SHERPA, and SD3-60 Airplanes, 67949-67952 [05-22305]
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67949
Federal Register / Vol. 70, No. 216 / Wednesday, November 9, 2005 / Proposed Rules
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Work hours
Average labor
rate per hour
Parts
Cost per airplane
Number of
U.S.-registered
airplanes
Fleet cost
Rivet installation .................................
1
$65
Operator-supplied ......
$65
108
$7,020
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
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.
Air transportation, Aircraft, Aviation
safety, Safety.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
VerDate Aug<31>2005
16:05 Nov 08, 2005
Jkt 208001
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Empresa Brasileira de Aeronautica S.A.
(EMBRAER): Docket No. FAA–2005–
22871; Directorate Identifier 2005–NM–
191–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by December 9, 2005.
Rivet Installation
(f) Within 4,000 flight hours or 24 months,
whichever occurs first after the effective date
of this AD: Install a rivet and washer in the
hole of the upper frame of the APU firewall,
in accordance with EMBRAER Service
Bulletin 120–53–0080, dated November 30,
2004.
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(h) Brazilian airworthiness directive 2005–
08–03, dated September 5, 2005, also
addresses the subject of this AD.
Issued in Renton, Washington, on October
26, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–22304 Filed 11–8–05; 8:45 am]
BILLING CODE 4910–13–U
Affected ADs
(b) None.
Applicability
DEPARTMENT OF TRANSPORTATION
(c) This AD applies to EMBRAER Model
EMB–120, –120ER, –120FC, –120QC, and
–120RT airplanes, certificated in any
category; as identified in EMBRAER Service
Bulletin 120–53–0080, dated November 30,
2004.
Federal Aviation Administration
Unsafe Condition
RIN 2120–AA64
(d) This AD results from a report indicating
that, during production, a pinhole was left
open at the upper frame of the auxiliary
power unit (APU) firewall. We are issuing
this AD to ensure that the APU compartment
is isolated from the rest of the airplane in the
event of an APU fire.
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.
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Frm 00019
Fmt 4702
Sfmt 4702
14 CFR Part 39
[Docket No. FAA–2005–22875; Directorate
Identifier 2005–NM–179–AD]
Airworthiness Directives; Short
Brothers Model SD3–60 SHERPA,
SD3–SHERPA, and SD3–60 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
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09NOP1
67950
Federal Register / Vol. 70, No. 216 / Wednesday, November 9, 2005 / Proposed Rules
directive (AD) that applies to all Short
Brothers Model SD3–60 and SD3–
SHERPA airplanes. The existing AD
currently requires an inspection of the
fork end of the rear pintle pin on each
main landing gear (MLG) to verify that
sealant is properly applied and is
undamaged, and related investigative/
corrective actions if necessary. This
proposed AD would add an inspection
for correctly applied sealant on the MLG
rear pintle pin assemblies, and related
investigative/corrective actions if
necessary. This proposed AD would
also expand the applicability of the
existing AD. This proposed AD results
from a new report of a cracked pintle
pin fork end. We are proposing this AD
to prevent stress-corrosion cracking and
subsequent failure of the MLG.
DATES: We must receive comments on
this proposed AD by December 9, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed 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 proposed
AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2005–22875;
Directorate Identifier 2005–NM–179–
AD’’ at the beginning of your comments.
We specifically invite comments on the
VerDate Aug<31>2005
16:05 Nov 08, 2005
Jkt 208001
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
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 proposed 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.
Discussion
On January 25, 1993, we issued AD
93–02–03, amendment 39–8485 (58 FR
7983, February 11, 1993), for all Short
Brothers Model SD3–60 and SD3–
SHERPA airplanes. That AD requires an
inspection of the fork end of the rear
pintle pin on each main landing gear
(MLG) to verify that sealant is properly
applied and is undamaged; removal of
the bushings and an inspection to detect
faults of the bores in the fork end, if
necessary; and repair of the fork end of
the pintle pin, if necessary. That AD
resulted from a report of a cracked fork
end of the MLG rear pintle pin. We
issued that AD to prevent stresscorrosion cracking and subsequent
failure of the MLG.
Actions Since Existing AD Was Issued
Since we issued AD 93–02–03, we
have learned about another incident of
a cracked pintle pin fork end on a
Model SD3 airplane.
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
Relevant Service Information
Shorts has issued Service Bulletins
SD360 Sherpa–32–4 (for Model SD3–60
SHERPA airplanes), SD3 Sherpa–32–5
(for Model SD3–SHERPA airplanes),
and SD360–32–37 (for Model SD3–60
airplanes), all dated July 2004. The
service bulletins describe procedures for
an inspection to determine whether
sealant has been properly applied on the
MLG rear pintle pin assemblies, and
related investigative/corrective actions
for missing or damaged sealant.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition. The Civil Aviation Authority
(CAA), which is the airworthiness
authority for the United Kingdom,
mandated the service information and
issued British airworthiness directive
G–2004–0022, dated August 25, 2004, to
ensure the continued airworthiness of
these airplanes in the United Kingdom.
The service bulletins refer to Messier
Dowty Service Bulletin 32–70SD,
Revision 1, dated July 3, 1995, as an
additional source of service information
for the inspection and related
investigative/corrective actions.
FAA’s Determination and Requirements
of the Proposed AD
These airplane models are
manufactured in the United Kingdom
and are 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 AD
action is necessary for airplanes of this
type design that are certificated for
operation in the United States.
This proposed AD would supersede
AD 93–02–03 and would retain the
requirements of the existing AD. This
proposed AD would also expand the
applicability for the actions specified in
service information described
previously, except as discussed below.
Difference Between the Proposed AD
and Service Information
The service information specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions using
a method that we or the CAA (or its
delegated agent) approve. In light of the
type of repair that would be required to
address the unsafe condition, and
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Federal Register / Vol. 70, No. 216 / Wednesday, November 9, 2005 / Proposed Rules
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
a repair we or the CAA approve would
be acceptable for compliance with this
proposed AD.
Clarification of Inspection Terminology
In this proposed AD, the inspection
specified in the service bulletins is
referred to as a ‘‘general visual
inspection.’’ Note 1 in this proposed AD
defines this type of inspection.
67951
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Inspection (required by AD 93–02–03) ....
Inspection (new proposed action) ............
1
1
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
VerDate Aug<31>2005
16:05 Nov 08, 2005
Average labor
rate
per hour
Work hours
Jkt 208001
Parts
$65
65
Cost per airplane
None
None
Number of
U.S.-registered
airplanes
$65
65
42
42
Fleet cost
$2,730
2,730
for a location to examine the regulatory
evaluation.
Restatement of Requirements of AD 93–02–
03
List of Subjects in 14 CFR Part 39
Inspection
(f) For Model SD3–60 and SD3–SHERPA
airplanes: Within 300 hours’ time-in-service
or 30 days after March 18, 1993 (the effective
date of AD 93–02–03), whichever occurs first,
perform a visual inspection of the fork end
of the rear pintle pin on each MLG to verify
that an undamaged fillet of sealant is
properly applied around the flanges of the
bronze bushings, in accordance with Shorts
SD3–60 Service Bulletin SD360–32–33, dated
August 7, 1992.
(1) If an undamaged fillet of properly
applied sealant is found: No further action is
required by this AD.
(2) If no fillet of sealant is found at the joint
line, or if a damaged fillet of sealant is found:
Prior to the accumulation of 1,200 hours’
time-in-service or 120 days after
accomplishing the inspection required by
paragraph (f) of this AD, whichever occurs
first, remove the bushings and perform a
magnetic non-destructive testing (NDT)
inspection to detect faults of the bores in the
fork end, in accordance with the service
bulletin. If faults are found as a result of the
NDT inspection, prior to further flight, repair
the fork end of the rear pintle pin in a
manner approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA.
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–8485 (58
FR 7983, February 11, 1993) and adding
the following new airworthiness
directive (AD):
Short Brothers PLC: Docket No. FAA–2005–
22875; Directorate Identifier 2005–NM–
179–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by December 9, 2005.
Affected ADs
(b) This AD supersedes AD 93–02–03.
Applicability
(c) This AD applies to all Shorts Model
SD3–60 SHERPA, SD3–SHERPA, and SD3–
60 airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a new report of
a cracked pintle pin fork end. We are issuing
this AD to prevent stress-corrosion cracking
and subsequent failure of the main landing
gear (MLG).
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.
PO 00000
Frm 00021
Fmt 4702
Sfmt 4702
New Requirements of This AD
Inspection
(g) For all airplanes: Within 3 months after
the effective date of this AD, do a general
visual inspection of the MLG rear pintle pin
assemblies for correctly applied sealant, in
accordance with Shorts Service Bulletin
SD360–32–37, SD3 SHERPA–32–5, or SD360
SHERPA 32–4, all dated July 2004, as
applicable.
(1) If the sealant is applied correctly: This
AD requires no further work.
(2) If the sealant is applied incorrectly:
Within 12 months after the effective date of
this AD, do a magnetic flaw detection
inspection to detect cracks of the rear pintle
pin fork ends, in accordance with the service
bulletin. If any cracked pintle pin fork end
is found: Replace it before further flight with
a serviceable part that has been inspected in
accordance with the requirements of this AD.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
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67952
Federal Register / Vol. 70, No. 216 / Wednesday, November 9, 2005 / Proposed Rules
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.’’
Notice of proposed rulemaking
(NPRM).
ACTION:
Airworthiness Directives; Boeing
Model 777–200 and –300 Series
Airplanes
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 777–200 and –300
series airplanes. This proposed AD
would require inspecting the lower web
of the aft fairing of engine struts for any
discoloration and doing any related
investigative and corrective action if
necessary; inspecting the heat shield
castings for any damage and doing any
corrective action if necessary; installing
gap cover strips; and replacing
insulation blankets with new insulation
blankets. This proposed AD results from
a report that several discolored fairing
lower webs and some damaged/
deteriorated insulation blankets were
found in the aft fairings of engine struts.
We are proposing this AD to prevent
cracking of lower webs of the aft
fairings, which could result in
flammable hydraulic fluid leaking onto
or near an ignition source, and possibly
result in an uncontrollable fire in the
engine strut area.
DATES: We must receive comments on
this proposed AD by December 27,
2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed 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 Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: John
Vann, Aerospace Engineer, Propulsion
Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6513;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
Note 2: The service bulletins identified in
paragraph (g) of this AD refer to Messier
Dowty Service Bulletin 32–70SD, Revision 1,
dated July 3, 1995, as an additional source of
service information for the inspection and
corrective actions.
(h) If any crack is detected during any
inspection required by this AD and the
service information specifies to contact the
manufacturer for repair instructions: Before
further flight, repair using a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the Civil
Aviation Authority (CAA) (or its delegated
agent).
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(j) British airworthiness directive G–2004–
0022, dated August 25, 2004, also addresses
the subject of this AD.
Issued in Renton, Washington, on October
28, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–22305 Filed 11–8–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22874; Directorate
Identifier 2005–NM–173–AD]
RIN 2120–AA64
AGENCY:
VerDate Aug<31>2005
16:05 Nov 08, 2005
Jkt 208001
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2005–22874; Directorate
Identifier 2005–NM–173–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
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 proposed 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 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.
Discussion
We have received a report indicating
that damaged/deteriorated thermal
insulation blankets and discolored
fairing lower webs were found in the aft
fairings of engine struts on several
Model 777–200 and –300 series
airplanes. Gaps in the segmented heat
shield in the strut aft fairings allow
engine primary/main exhaust to enter
the heat shield cavity in the strut aft
fairing. The temperature of the exhaust
that leaks into the heat shield cavity
exceeds the insulation blankets’
maximum design tolerance. Since the
insulation blankets provide thermal
protection for the aluminum fairing
lower web, degradation of an insulation
blanket allows thermal distress of the
lower web and eventually, cracking of
the lower web. A cracked lower web is
E:\FR\FM\09NOP1.SGM
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]]>Agencies
[Federal Register Volume 70, Number 216 (Wednesday, November 9, 2005)]
[Proposed Rules]
[Pages 67949-67952]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-22305]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22875; Directorate Identifier 2005-NM-179-AD]
RIN 2120-AA64
Airworthiness Directives; Short Brothers Model SD3-60 SHERPA,
SD3-SHERPA, and SD3-60 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
[[Page 67950]]
directive (AD) that applies to all Short Brothers Model SD3-60 and SD3-
SHERPA airplanes. The existing AD currently requires an inspection of
the fork end of the rear pintle pin on each main landing gear (MLG) to
verify that sealant is properly applied and is undamaged, and related
investigative/corrective actions if necessary. This proposed AD would
add an inspection for correctly applied sealant on the MLG rear pintle
pin assemblies, and related investigative/corrective actions if
necessary. This proposed AD would also expand the applicability of the
existing AD. This proposed AD results from a new report of a cracked
pintle pin fork end. We are proposing this AD to prevent stress-
corrosion cracking and subsequent failure of the MLG.
DATES: We must receive comments on this proposed AD by December 9,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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 proposed AD.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2005-22875; Directorate Identifier 2005-NM-179-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
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 proposed 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.
Discussion
On January 25, 1993, we issued AD 93-02-03, amendment 39-8485 (58
FR 7983, February 11, 1993), for all Short Brothers Model SD3-60 and
SD3-SHERPA airplanes. That AD requires an inspection of the fork end of
the rear pintle pin on each main landing gear (MLG) to verify that
sealant is properly applied and is undamaged; removal of the bushings
and an inspection to detect faults of the bores in the fork end, if
necessary; and repair of the fork end of the pintle pin, if necessary.
That AD resulted from a report of a cracked fork end of the MLG rear
pintle pin. We issued that AD to prevent stress-corrosion cracking and
subsequent failure of the MLG.
Actions Since Existing AD Was Issued
Since we issued AD 93-02-03, we have learned about another incident
of a cracked pintle pin fork end on a Model SD3 airplane.
Relevant Service Information
Shorts has issued Service Bulletins SD360 Sherpa-32-4 (for Model
SD3-60 SHERPA airplanes), SD3 Sherpa-32-5 (for Model SD3-SHERPA
airplanes), and SD360-32-37 (for Model SD3-60 airplanes), all dated
July 2004. The service bulletins describe procedures for an inspection
to determine whether sealant has been properly applied on the MLG rear
pintle pin assemblies, and related investigative/corrective actions for
missing or damaged sealant. Accomplishing the actions specified in the
service information is intended to adequately address the unsafe
condition. The Civil Aviation Authority (CAA), which is the
airworthiness authority for the United Kingdom, mandated the service
information and issued British airworthiness directive G-2004-0022,
dated August 25, 2004, to ensure the continued airworthiness of these
airplanes in the United Kingdom.
The service bulletins refer to Messier Dowty Service Bulletin 32-
70SD, Revision 1, dated July 3, 1995, as an additional source of
service information for the inspection and related investigative/
corrective actions.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in the United Kingdom and
are 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 AD
action is necessary for airplanes of this type design that are
certificated for operation in the United States.
This proposed AD would supersede AD 93-02-03 and would retain the
requirements of the existing AD. This proposed AD would also expand the
applicability for the actions specified in service information
described previously, except as discussed below.
Difference Between the Proposed AD and Service Information
The service information specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions using a method that we or the
CAA (or its delegated agent) approve. In light of the type of repair
that would be required to address the unsafe condition, and
[[Page 67951]]
consistent with existing bilateral airworthiness agreements, we have
determined that, for this proposed AD, a repair we or the CAA approve
would be acceptable for compliance with this proposed AD.
Clarification of Inspection Terminology
In this proposed AD, the inspection specified in the service
bulletins is referred to as a ``general visual inspection.'' Note 1 in
this proposed AD defines this type of inspection.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 93-02-03).................... 1 $65 None $65 42 $2,730
Inspection (new proposed action)........................ 1 65 None 65 42 2,730
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-8485 (58 FR 7983, February 11, 1993) and adding
the following new airworthiness directive (AD):
Short Brothers PLC: Docket No. FAA-2005-22875; Directorate
Identifier 2005-NM-179-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
9, 2005.
Affected ADs
(b) This AD supersedes AD 93-02-03.
Applicability
(c) This AD applies to all Shorts Model SD3-60 SHERPA, SD3-
SHERPA, and SD3-60 airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a new report of a cracked pintle pin
fork end. We are issuing this AD to prevent stress-corrosion
cracking and subsequent failure of the main landing gear (MLG).
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.
Restatement of Requirements of AD 93-02-03
Inspection
(f) For Model SD3-60 and SD3-SHERPA airplanes: Within 300 hours'
time-in-service or 30 days after March 18, 1993 (the effective date
of AD 93-02-03), whichever occurs first, perform a visual inspection
of the fork end of the rear pintle pin on each MLG to verify that an
undamaged fillet of sealant is properly applied around the flanges
of the bronze bushings, in accordance with Shorts SD3-60 Service
Bulletin SD360-32-33, dated August 7, 1992.
(1) If an undamaged fillet of properly applied sealant is found:
No further action is required by this AD.
(2) If no fillet of sealant is found at the joint line, or if a
damaged fillet of sealant is found: Prior to the accumulation of
1,200 hours' time-in-service or 120 days after accomplishing the
inspection required by paragraph (f) of this AD, whichever occurs
first, remove the bushings and perform a magnetic non-destructive
testing (NDT) inspection to detect faults of the bores in the fork
end, in accordance with the service bulletin. If faults are found as
a result of the NDT inspection, prior to further flight, repair the
fork end of the rear pintle pin in a manner approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA.
New Requirements of This AD
Inspection
(g) For all airplanes: Within 3 months after the effective date
of this AD, do a general visual inspection of the MLG rear pintle
pin assemblies for correctly applied sealant, in accordance with
Shorts Service Bulletin SD360-32-37, SD3 SHERPA-32-5, or SD360
SHERPA 32-4, all dated July 2004, as applicable.
(1) If the sealant is applied correctly: This AD requires no
further work.
(2) If the sealant is applied incorrectly: Within 12 months
after the effective date of this AD, do a magnetic flaw detection
inspection to detect cracks of the rear pintle pin fork ends, in
accordance with the service bulletin. If any cracked pintle pin fork
end is found: Replace it before further flight with a serviceable
part that has been inspected in accordance with the requirements of
this AD.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual
[[Page 67952]]
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.''
Note 2: The service bulletins identified in paragraph (g) of
this AD refer to Messier Dowty Service Bulletin 32-70SD, Revision 1,
dated July 3, 1995, as an additional source of service information
for the inspection and corrective actions.
(h) If any crack is detected during any inspection required by
this AD and the service information specifies to contact the
manufacturer for repair instructions: Before further flight, repair
using a method approved by either the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the Civil Aviation
Authority (CAA) (or its delegated agent).
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(j) British airworthiness directive G-2004-0022, dated August
25, 2004, also addresses the subject of this AD.
Issued in Renton, Washington, on October 28, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-22305 Filed 11-8-05; 8:45 am]
BILLING CODE 4910-13-P
