Airworthiness Directives; Lockheed Model 1329 Series Airplanes, 29088-29091 [E7-10033]
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Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules
hand) hinge fittings due to stress corrosion
on in-service aircraft. If undetected, they
could lead to complete rupture of one or two
of the fittings.
The unsafe condition is collapse of the nose
landing gear. The MCAI requires repetitive
inspections of the nose landing gear LH and
RH hinge fittings for cracking, and replacing
the hinge fitting with a new fitting if any
cracking is found.
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 200 flight hours or 6 months
after the effective date of this AD, whichever
occurs first: Inspect the nose landing gear LH
(left-hand) and RH (right-hand) hinge fittings
for cracking, in accordance with the
instructions of Airbus SN–601 Corvette
Service Bulletin 32–17, dated September 23,
2004.
(2) In case of finding one or several cracks,
before further flight, replace the hinge fitting
with a new hinge fitting in accordance with
the instructions of Airbus SN–601 Corvette
Service Bulletin 32–17, dated September 23,
2004. Repeat the requirements of paragraph
(f)(1) of this AD thereafter at intervals not to
exceed 3,600 flight hours or 36 months,
whichever occurs first.
(3) If no crack is detected, repeat the
requirements of paragraph (f)(1) of this AD
thereafter at intervals not to exceed 3,600
flight hours or 36 months, whichever occurs
first.
Issued in Renton, Washington, on May 15,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10046 Filed 5–23–07; 8:45 am]
FAA AD Differences
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Note: This AD differs from the MCAI and/
or service information as follows: Although
the MCAI or service information allows
further flight after cracks are found during
compliance with the required action,
paragraph (f)(2) of this AD requires that you
repair the cracks before further flight.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Mike Borfitz,
Aerospace Engineer, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–2677; fax (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
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Related Information
(h) Refer to MCAI French Airworthiness
Directive F–2004–169, dated October 27,
2004; and Airbus SN–601 Corvette Service
Bulletin 32–17, dated September 23, 2004;
for related information.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28255; Directorate
Identifier 2007–NM–023–AD]
RIN 2120–AA64
Airworthiness Directives; Lockheed
Model 1329 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Lockheed Model 1329 series
airplanes. This proposed AD would
require determining the part number on
the steering cylinder assembly for the
nose landing gear (NLG), determining
the total flight cycles accumulated on
the NLG steering cylinder assembly,
repetitive replacement of the assembly,
inspecting for missing tow turning limit
markings, and performing corrective
actions if necessary. This proposed AD
results from reports of numerous
failures of the NLG steering cylinder.
We are proposing this AD to prevent the
loss of hydraulic pressure and steering
control.
DATES: We must receive comments on
this proposed AD by June 25, 2007.
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
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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 Lockheed Martin Aircraft &
Logistics Center, 120 Orion Street,
Greenville, South Carolina 29605, for
the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT:
Hector Hernandez, Aerospace Engineer,
Systems and Equipment Branch, ACE–
119A, FAA, Atlanta Aircraft
Certification Office, One Crown Center,
1895 Phoenix Boulevard, Suite 450,
Atlanta, Georgia 30349; telephone (770)
703–6069; fax (770) 703–6097.
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 ‘‘FAA–2007–28255; Directorate
Identifier 2007–NM–023–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
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Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules
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 reports of numerous
failures of the nose landing gear (NLG)
steering cylinder on Lockheed Model
1329 series airplanes. These failures
have been attributed to stress corrosion
cracking, compounded by towing of the
aircraft and exceeding the allowable
turn limits with the scissor links
connected. The manufacturer has
reviewed service history and performed
structural analysis on the cylinder
29089
assembly. Failure of the steering
cylinder, if not corrected, could result in
the loss of hydraulic pressure and
steering control.
Relevant Service Information
We have reviewed the Lockheed
service bulletins identified in the
following table.
SERVICE BULLETINS
Service bulletin
Revision
Date
Affected airplanes
329–300 .......................
329II–32–8 ...................
C ..............
B ..............
September 5, 2006 ..............................................................................
September 5, 2006 ..............................................................................
1329–23A, 1329–23D, 1329–23E.
1329–25.
The service bulletins describe
procedures for the following actions:
• Inspecting the NLG steering
cylinder assembly for the installed part
number;
• Removing from service NLG
steering cylinder assemblies, part
number (P/N) JL1955–1 and JL1955–3;
• Reviewing airplane records to
determine the total flight cycles
accumulated on the cylinder assembly;
• Removing from service those
cylinders that have exceeded their life
limit;
• Establishing life limits (including a
repetitive replacement schedule) for all
other part-numbered cylinder
assemblies (as set forth in the Life
Limits table below);
• Replacing, with new parts, any
cylinder assembly if its part number is
JL1955–1 or JL1955–3 or its
components’ life limits have been
exceeded;
• Inspecting the exterior fuselage to
confirm that the tow turning limit
markings are present on the airplane;
and
• Restoring/applying the markings.
JETSTAR NLG STEERING CYLINDER ASSEMBLY LIFE LIMITS
Component
Part No.
7049–T73 die forging .................................................................................................................................................
7050–T7451 plate ......................................................................................................................................................
4340 steel bar ............................................................................................................................................................
15–5PH plate .............................................................................................................................................................
JL1955–7 ....
JL1955–9 ....
JL1955–801
JL1955–13 ..
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of this same
type design. For this reason, we are
proposing this AD, which would require
accomplishing the actions specified in
the service information described
previously.
We have determined that a reliable
inspection of the subject area is not
possible. Because the initial detectable
crack is longer than the critical crack
length in this case, we cannot show
crack growth using damage tolerance
analysis or develop appropriate
inspection intervals. Further,
disassembling the actuator steering
cylinder—the only possible way to
Life limit
(in flight
cycles)
2,100
1,075
3,100
>1,000,000
perform the inspection—would destroy
the cylinder. As a result of service
history and engineering evaluation, a
fatigue-based life limit of the actuator
steering cylinder is necessary to ensure
the continued airworthiness of the fleet.
Costs of Compliance
There are about 48 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Average labor
rate per hour
Parts
Cost per
airplane
Number of
U.S.-registered
airplanes
Fleet cost
3 ...........................................................................................
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Work hours
$80
$0
$240
34
$8,160
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
VerDate Aug<31>2005
15:42 May 23, 2007
Jkt 211001
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
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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
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Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules
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:
Comments Due Date
(a) The FAA must receive comments on
this AD action by June 25, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
airplanes, certificated in any category.
(1) Lockheed Model 1329–23A, 1329–23D,
and 1329–23E series airplanes; serial
numbers 5001 through 5162 inclusive.
(2) Lockheed Model 1329–25 series
airplanes, serial numbers 5201 through 5240
inclusive.
Unsafe Condition
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
(d) This AD results from reports of
numerous failures of the nose landing gear
(NLG) steering cylinder. We are issuing this
AD to prevent the loss of hydraulic pressure
and steering control.
Compliance
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):
Lockheed: Docket No. FAA–2007–28255;
Directorate Identifier 2007–NM–023–AD.
(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 Information
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of the applicable service bulletin
identified in Table 1 of this AD.
TABLE 1.—SERVICE BULLETINS
Lockheed
service bulletin
Revision
Date
Affected airplanes
329–300 .......................
329II–32–8 ...................
C ..............
B ..............
September 5, 2006 ..............................................................................
September 5, 2006 ..............................................................................
1329–23A, 1329–23D, 1329–23E.
1329–25.
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Inspection for Cylinder Assembly Part
Number
(g) Within 30 days after the effective date
of this AD, inspect to determine the part
number (P/N) on the steering cylinder
assembly for the nose landing gear (NLG). A
review of airplane maintenance records is
acceptable in lieu of this inspection if the
part number can be conclusively determined
from that review. Replace any cylinder
assembly having P/N JL1955–1 or JL1955–3
with a new assembly before further flight in
accordance with the applicable service
bulletin.
Life Limits
(h) Within 30 days after the effective date
of this AD: Review the airplane records to
determine the total flight cycles accumulated
on the NLG steering cylinder assembly, in
accordance with the applicable service
bulletin. Before any steering cylinder
assembly component reaches its life limit, as
specified in Table 1 of the Accomplishment
Instructions of the applicable service
bulletin, or within 30 days after the effective
date of this AD, whichever occurs later:
Replace the cylinder assembly with a new
assembly in accordance with the applicable
service bulletin. If the steering cylinder
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15:42 May 23, 2007
Jkt 211001
assembly’s age cannot be positively
determined from the records review, replace
it within 30 days after the effective date of
this AD, in accordance with the applicable
service bulletin. Thereafter, replace the
cylinder assembly at intervals not to exceed
the life limits as specified in the applicable
service bulletin.
Inspection for Tow Turning Limit Markings
(i) Within 30 days after the effective date
of this AD: Perform a general visual
inspection above the NLG doors to detect
missing tow turning limit markings, in
accordance with the applicable service
bulletin. If any markings are absent, restore/
apply markings before further flight in
accordance with the applicable service
bulletin.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
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
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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.’’
Parts Installation
(j) As of the effective date of this AD, do
not install on any airplane a NLG steering
cylinder assembly that has P/N JL1955–1 or
JL1955–3.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Atlanta Aircraft
Certification Office (ACO), 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.
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Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules
Issued in Renton, Washington, on May 15,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10033 Filed 5–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28256; Directorate
Identifier 2007–NM–041–AD]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135BJ
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
SUMMARY:
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It has been found the occurrence of smoke
on the passenger cabin originated from the
valance panel lighting system wiring.
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by June 25, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• 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.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
VerDate Aug<31>2005
15:42 May 23, 2007
Jkt 211001
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
proposed AD, the regulatory evaluation,
any comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–28256; Directorate Identifier
2007–NM–041–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on 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
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29091
substantive verbal contact we receive
about this proposed AD.
Discussion
ˆ
The Agencia Nacional de Aviacao
¸˜
Civil (ANAC), which is the aviation
authority for Brazil, has issued Brazilian
Airworthiness Directive 2007–01–03,
effective January 22, 2007 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
It has been found the occurrence of smoke
on the passenger cabin originated from the
valance panel lighting system wiring.
The corrective action is replacement of
the valance panel lighting system
wiring. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
EMBRAER has issued Service Bulletin
145LEG–25–0070, dated October 11,
2006. The actions described in this
service information are intended to
correct the unsafe condition identified
in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a NOTE within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
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]]>Agencies
[Federal Register Volume 72, Number 100 (Thursday, May 24, 2007)]
[Proposed Rules]
[Pages 29088-29091]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10033]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28255; Directorate Identifier 2007-NM-023-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model 1329 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Lockheed Model 1329 series airplanes. This proposed AD
would require determining the part number on the steering cylinder
assembly for the nose landing gear (NLG), determining the total flight
cycles accumulated on the NLG steering cylinder assembly, repetitive
replacement of the assembly, inspecting for missing tow turning limit
markings, and performing corrective actions if necessary. This proposed
AD results from reports of numerous failures of the NLG steering
cylinder. We are proposing this AD to prevent the loss of hydraulic
pressure and steering control.
DATES: We must receive comments on this proposed AD by June 25, 2007.
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 Lockheed Martin Aircraft & Logistics Center, 120 Orion
Street, Greenville, South Carolina 29605, for the service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Hector Hernandez, Aerospace Engineer,
Systems and Equipment Branch, ACE-119A, FAA, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite
450, Atlanta, Georgia 30349; telephone (770) 703-6069; fax (770) 703-
6097.
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 ``FAA-2007-
28255; Directorate Identifier 2007-NM-023-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
[[Page 29089]]
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 reports of numerous failures of the nose landing
gear (NLG) steering cylinder on Lockheed Model 1329 series airplanes.
These failures have been attributed to stress corrosion cracking,
compounded by towing of the aircraft and exceeding the allowable turn
limits with the scissor links connected. The manufacturer has reviewed
service history and performed structural analysis on the cylinder
assembly. Failure of the steering cylinder, if not corrected, could
result in the loss of hydraulic pressure and steering control.
Relevant Service Information
We have reviewed the Lockheed service bulletins identified in the
following table.
Service Bulletins
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision Date Affected airplanes
----------------------------------------------------------------------------------------------------------------
329-300........................ C.............. September 5, 2006 1329-23A, 1329-23D, 1329-23E.
329II-32-8..................... B.............. September 5, 2006 1329-25.
----------------------------------------------------------------------------------------------------------------
The service bulletins describe procedures for the following
actions:
Inspecting the NLG steering cylinder assembly for the
installed part number;
Removing from service NLG steering cylinder assemblies,
part number (P/N) JL1955-1 and JL1955-3;
Reviewing airplane records to determine the total flight
cycles accumulated on the cylinder assembly;
Removing from service those cylinders that have exceeded
their life limit;
Establishing life limits (including a repetitive
replacement schedule) for all other part-numbered cylinder assemblies
(as set forth in the Life Limits table below);
Replacing, with new parts, any cylinder assembly if its
part number is JL1955-1 or JL1955-3 or its components' life limits have
been exceeded;
Inspecting the exterior fuselage to confirm that the tow
turning limit markings are present on the airplane; and
Restoring/applying the markings.
Jetstar NLG Steering Cylinder Assembly Life Limits
------------------------------------------------------------------------
Life limit
Component Part No. (in flight
cycles)
------------------------------------------------------------------------
7049-T73 die forging............. JL1955-7............. 2,100
7050-T7451 plate................. JL1955-9............. 1,075
4340 steel bar................... JL1955-801........... 3,100
15-5PH plate..................... JL1955-13............ >1,000,000
------------------------------------------------------------------------
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously.
We have determined that a reliable inspection of the subject area
is not possible. Because the initial detectable crack is longer than
the critical crack length in this case, we cannot show crack growth
using damage tolerance analysis or develop appropriate inspection
intervals. Further, disassembling the actuator steering cylinder--the
only possible way to perform the inspection--would destroy the
cylinder. As a result of service history and engineering evaluation, a
fatigue-based life limit of the actuator steering cylinder is necessary
to ensure the continued airworthiness of the fleet.
Costs of Compliance
There are about 48 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
3.................................................................. $80 $0 $240 34 $8,160
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
[[Page 29090]]
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
adding the following new airworthiness directive (AD):
Lockheed: Docket No. FAA-2007-28255; Directorate Identifier 2007-NM-
023-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by June 25,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplanes, certificated in
any category.
(1) Lockheed Model 1329-23A, 1329-23D, and 1329-23E series
airplanes; serial numbers 5001 through 5162 inclusive.
(2) Lockheed Model 1329-25 series airplanes, serial numbers 5201
through 5240 inclusive.
Unsafe Condition
(d) This AD results from reports of numerous failures of the
nose landing gear (NLG) steering cylinder. We are issuing this AD to
prevent the loss of hydraulic pressure and steering control.
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 Information
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the applicable service bulletin
identified in Table 1 of this AD.
Table 1.--Service Bulletins
----------------------------------------------------------------------------------------------------------------
Lockheed service bulletin Revision Date Affected airplanes
----------------------------------------------------------------------------------------------------------------
329-300........................ C.............. September 5, 2006 1329-23A, 1329-23D, 1329-23E.
329II-32-8..................... B.............. September 5, 2006 1329-25.
----------------------------------------------------------------------------------------------------------------
Inspection for Cylinder Assembly Part Number
(g) Within 30 days after the effective date of this AD, inspect
to determine the part number (P/N) on the steering cylinder assembly
for the nose landing gear (NLG). A review of airplane maintenance
records is acceptable in lieu of this inspection if the part number
can be conclusively determined from that review. Replace any
cylinder assembly having P/N JL1955-1 or JL1955-3 with a new
assembly before further flight in accordance with the applicable
service bulletin.
Life Limits
(h) Within 30 days after the effective date of this AD: Review
the airplane records to determine the total flight cycles
accumulated on the NLG steering cylinder assembly, in accordance
with the applicable service bulletin. Before any steering cylinder
assembly component reaches its life limit, as specified in Table 1
of the Accomplishment Instructions of the applicable service
bulletin, or within 30 days after the effective date of this AD,
whichever occurs later: Replace the cylinder assembly with a new
assembly in accordance with the applicable service bulletin. If the
steering cylinder assembly's age cannot be positively determined
from the records review, replace it within 30 days after the
effective date of this AD, in accordance with the applicable service
bulletin. Thereafter, replace the cylinder assembly at intervals not
to exceed the life limits as specified in the applicable service
bulletin.
Inspection for Tow Turning Limit Markings
(i) Within 30 days after the effective date of this AD: Perform
a general visual inspection above the NLG doors to detect missing
tow turning limit markings, in accordance with the applicable
service bulletin. If any markings are absent, restore/apply markings
before further flight in accordance with the applicable service
bulletin.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual 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.''
Parts Installation
(j) As of the effective date of this AD, do not install on any
airplane a NLG steering cylinder assembly that has P/N JL1955-1 or
JL1955-3.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Atlanta Aircraft Certification Office (ACO),
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.
[[Page 29091]]
Issued in Renton, Washington, on May 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10033 Filed 5-23-07; 8:45 am]
BILLING CODE 4910-13-P
