Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 58906-58908 [E8-23828]
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58906
Federal Register / Vol. 73, No. 196 / Wednesday, October 8, 2008 / Proposed Rules
(3) Apply BMS 10–86 Teflon-filled coating.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN: Ivan
Li, Aerospace Engineer, Airframe Branch,
ANM–120S, FAA, Seattle ACO, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 917–6437; fax (425)
917–6590; has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Issued in Renton, Washington, on
September 26, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–23824 Filed 10–7–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1070; Directorate
Identifier 2008–NM–087–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
dwashington3 on PRODPC61 with PROPOSALS
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for all
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
For all airplanes, this proposed AD
would require repetitive overhaul of the
retract actuator beam of the main
landing gear (MLG). For certain
VerDate Aug<31>2005
14:29 Oct 07, 2008
Jkt 217001
airplanes, this proposed AD would
require repetitive inspections for
damage of the retract actuator beam, and
related investigative and corrective
actions if necessary. This proposed AD
results from reports of broken retract
actuator beams of the MLG and the
subsequent failure of the MLG to fully
retract. We are proposing this AD to
detect and correct broken retract
actuator beams of the MLG, which could
cause damage to the beam arm,
hydraulic tubing, and flight control
cables. Damage to the flight control
cables could result in loss of control of
the airplane.
DATES: We must receive comments on
this proposed AD by November 24,
2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.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 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590.
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SUPPLEMENTARY INFORMATION:
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–2008–1070; Directorate Identifier
2008–NM–087–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 because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received reports of broken
retract actuator beams of the main
landing gear (MLG) and the subsequent
failure of the MLG to fully retract. In
one incident, hydraulic system A
became unserviceable. In another
incident, the flightcrew declared an
emergency and made an air turn-back.
For all the reports of MLG retract
actuator beams that broke in service, the
MLG fell to the down-and-locked
position, and landings were normal.
Investigation revealed that proper
procedures were not followed during
overhaul, resulting in stress corrosion
cracking initiating from small corrosion
pits that were not entirely removed. In
one incident, cracking initiated in an
area of heat damage/burning caused by
incorrect stylus cadmium plating.
Broken retract actuator beams of the
MLG, if not corrected, could cause
damage to the beam arm, hydraulic
tubing, and flight control cables.
Damage to the flight control cables
could result in loss of control of the
airplane.
Relevant Service Information
We have reviewed Boeing Service
Bulletin 737–32A1355, Revision 2,
dated March 5, 2008. The service
bulletin describes the procedures and
compliance times specified in the
following service information table.
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08OCP1
Federal Register / Vol. 73, No. 196 / Wednesday, October 8, 2008 / Proposed Rules
58907
SERVICE INFORMATION
Applicability description
Actions
Compliance time
All airplanes ........................................................
An overhaul of the beam is performed and improved finishes are applied. New fittings,
bushings and bearings are installed. The lubrication passages must be cleared. The
related investigative and corrective actions,
if necessary, include a special detailed inspection for corrosion pits or damage of the
beam, and repair before further flight.
A general visual inspection (GVI) of the beam
is performed for damage, finish degradation, and corrosion. The related investigative and corrective actions, if necessary, include a special detailed inspection for corrosion pits or damage of the beam, and repair before further flight.
Within 180 days after the date of this service
bulletin, or within 10 years from the date of
the most recent overhaul of the beam,
whichever occurs later. Repeat interval is
not to exceed 10 years after the last overhaul.
2008, does not specify a compliance
time for repairing the retract actuator
beam if damage, finish degradation, or
corrosion is found. This proposed AD
would require that those repairs be done
before further flight after accomplishing
the applicable inspections.
Boeing Service Bulletin 737–
32A1355, Revision 2, dated March 5,
2008, specifies that the actions are for
airplanes with new MLG retract actuator
beams having P/N 65–46108–15 and
subsequent dash numbers that have not
been overhauled, and new or
overhauled MLG retract actuator beams
having P/N 65–46108–14 and previous
dash numbers. However, MLG retract
actuator beams which are not new or
overhauled may also exhibit the
identified unsafe condition. For this
reason, this proposed AD is not limited
to new or overhauled beams; the
proposed AD would require that the
actions be done on airplanes having any
MLG retract actuator beam having one
of those P/Ns. This correction will be
included in the next revision of the
service bulletin.
We have coordinated these
differences with the manufacturer.
Group 1, Configuration 3 airplanes with a MLG
retract actuator beam having part number (P/
N) 65–46108–14 and previous dash numbers
that have not incorporated the original issue,
Revision 1, or Revision 2 of the service bulletin.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design. This proposed AD would
require accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Differences Between
the Proposed AD and Service
Information.’’
Differences Between the Proposed AD
and Service Information
Boeing Service Bulletin 737–
32A1355, Revision 2, dated March 5,
Within 2 years after the date of this service
bulletin. Repeat interval is not to exceed 2
years after the last inspection.
Costs of Compliance
We estimate that this proposed AD
would affect 652 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action/airplane group
Average labor
rate per hour
Work hours
Overhaul for Group 1; Configurations 1, 2, and 3.
Inspection for Group 1, Configuration 3.
dwashington3 on PRODPC61 with PROPOSALS
Fleet cost
$80
None ............
$5,120, per overhaul cycle ..
652
$3,338,240
1
80
None ............
$80, per inspection cycle ....
525
42,000
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
14:29 Oct 07, 2008
Number of
U.S.-registered
airplanes
Cost per product
64
Authority for This Rulemaking
VerDate Aug<31>2005
Parts cost
Jkt 217001
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 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
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this 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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
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58908
Federal Register / Vol. 73, No. 196 / Wednesday, October 8, 2008 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Boeing: Docket No. FAA–2008–1070;
Directorate Identifier 2008-NM–087–AD.
Comments Due Date
(a) We must receive comments by
November 24, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model
737–100, –200, –200C, –300, –400, and –500
series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from reports of broken
retract actuator beams of the main landing
gear (MLG) and the subsequent failure of the
MLG to fully retract. We are issuing this AD
to detect and correct broken retract actuator
beams of the MLG, which could result in
damage to the beam arm, hydraulic tubing,
and flight control cables. Damage to the flight
control cables could result in loss of control
of the airplane.
dwashington3 on PRODPC61 with PROPOSALS
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Inspection and Related Investigative and
Corrective Actions/Overhaul
(f) Except as provided by paragraphs (g)
and (h) of this AD: At the applicable times
specified in paragraph 1.E. of Boeing Service
Bulletin 737–32A1355, Revision 2, dated
March 5, 2008; inspect for damage of the
retract actuator beam of the MLG and
overhaul the retract actuator beam, as
applicable, by doing all the applicable
actions specified in the Accomplishment
Instructions of the service bulletin. Do all
applicable related investigative and
corrective actions before further flight.
Repeat the applicable inspection or overhaul
thereafter at the applicable time specified in
paragraph 1.E. of the service bulletin.
Exceptions to Service Information
(g) Where Boeing Service Bulletin 737–
32A1355, Revision 2, dated March 5, 2008,
specifies a compliance time after ‘‘* * * the
date on this service bulletin,’’ this AD
VerDate Aug<31>2005
14:29 Oct 07, 2008
Jkt 217001
requires compliance within the specified
compliance time after the effective date of
this AD.
(h) Boeing Service Bulletin 737–32A1355,
Revision 2, dated March 5, 2008, specifies
that the actions are for airplanes with new
MLG retract actuator beams that have not
been overhauled having P/N 65–46108–15
and subsequent dash numbers, and new or
overhauled MLG retract actuator beams
having P/N 65–46108–14 and previous dash
numbers; however, this AD is not limited to
new or overhauled beams. This AD requires
that the actions required by paragraph (f) of
this AD be done on airplanes with any MLG
retract actuator beam having those P/Ns.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Nancy Marsh, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved the repair must meet the
certification basis of the airplane and the
approval must specifically refer to this AD.
Issued in Renton, Washington, on
September 26, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–23828 Filed 10–7–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Highway Administration
23 CFR Parts 620, 635, 636, and 710
[FHWA Docket No. FHWA–2008–0136]
RIN 2125–AF29
SUMMARY: This NPRM proposes to
amend FHWA regulations, to require
State departments of transportation
(DOT) and other public authorities to
negotiate for and obtain fair market
value as part of any concession
agreement involving a facility acquired
or constructed with Federal-aid
highway funds. Additionally, this
NPRM proposes to amend FHWA
regulations to permit public agencies to
compete against private entities for the
right to obtain a concession agreement
involving such facilities. Also, this
notice proposes to amend the designbuild regulations to permit contracting
agencies to incorporate unsuccessful
offerors’ ideas into a design-build
contract upon the acceptance of a
stipend.
Comments must be received on
or before November 7, 2008. Late-filed
comments will be considered to the
extent practicable.
ADDRESSES: Mail or hand deliver
comments to the U.S. Department of
Transportation, Dockets Management
Facility, Room PL–401, 400 Seventh
Street, SW., Washington, DC 20590, or
submit electronically at https://
dms.dot.gov/submit or fax comments to
(202) 493–2251.
Alternatively, comments may be
submitted to the Federal eRulemaking
portal at https://www.regulations.gov. All
comments should include the docket
number that appears in the heading of
this document. All comments received
will be available for examination and
copying at the above address from 9
a.m. to 5 p.m., e.t., Monday through
Friday, except Federal holidays. Those
desiring notification of receipt of
comments must include a selfaddressed, stamped postcard or you
may print the acknowledgment page
that appears after submitting comments
electronically. Anyone is able to search
the electronic form of all comments in
any of our dockets by the name of the
individual submitting the comment (or
signing the comment, if submitted on
behalf of an association, business, or
labor union). You may review DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (Volume 65, Number 70, Pages
19477–78) or you may visit https://
dms.dot.gov.
DATES:
Mr.
Marcus J. Lemon, Chief Counsel, Mr.
Michael Harkins, Office of Chief
Counsel, or Mr. Steve Rochlis, Office of
Chief Counsel, (202) 366–0740, Federal
Highway Administration, 1200 New
Jersey Avenue, SE., Washington, DC
20590–0001. Office hours are from 7:45
FOR FURTHER INFORMATION CONTACT:
Fair Market Value and Design-Build
Amendments
Federal Highway
Administration (FHWA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM); request for comments.
AGENCY:
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E:\FR\FM\08OCP1.SGM
08OCP1
]]>Agencies
[Federal Register Volume 73, Number 196 (Wednesday, October 8, 2008)]
[Proposed Rules]
[Pages 58906-58908]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-23828]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1070; Directorate Identifier 2008-NM-087-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Boeing Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. For all airplanes, this proposed AD would require repetitive
overhaul of the retract actuator beam of the main landing gear (MLG).
For certain airplanes, this proposed AD would require repetitive
inspections for damage of the retract actuator beam, and related
investigative and corrective actions if necessary. This proposed AD
results from reports of broken retract actuator beams of the MLG and
the subsequent failure of the MLG to fully retract. We are proposing
this AD to detect and correct broken retract actuator beams of the MLG,
which could cause damage to the beam arm, hydraulic tubing, and flight
control cables. Damage to the flight control cables could result in
loss of control of the airplane.
DATES: We must receive comments on this proposed AD by November 24,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.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 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6440; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
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-2008-1070;
Directorate Identifier 2008-NM-087-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 because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of broken retract actuator beams of the
main landing gear (MLG) and the subsequent failure of the MLG to fully
retract. In one incident, hydraulic system A became unserviceable. In
another incident, the flightcrew declared an emergency and made an air
turn-back. For all the reports of MLG retract actuator beams that broke
in service, the MLG fell to the down-and-locked position, and landings
were normal. Investigation revealed that proper procedures were not
followed during overhaul, resulting in stress corrosion cracking
initiating from small corrosion pits that were not entirely removed. In
one incident, cracking initiated in an area of heat damage/burning
caused by incorrect stylus cadmium plating. Broken retract actuator
beams of the MLG, if not corrected, could cause damage to the beam arm,
hydraulic tubing, and flight control cables. Damage to the flight
control cables could result in loss of control of the airplane.
Relevant Service Information
We have reviewed Boeing Service Bulletin 737-32A1355, Revision 2,
dated March 5, 2008. The service bulletin describes the procedures and
compliance times specified in the following service information table.
[[Page 58907]]
Service Information
----------------------------------------------------------------------------------------------------------------
Applicability description Actions Compliance time
----------------------------------------------------------------------------------------------------------------
All airplanes.................... An overhaul of the beam is performed Within 180 days after the date of
and improved finishes are applied. this service bulletin, or within 10
New fittings, bushings and bearings years from the date of the most
are installed. The lubrication recent overhaul of the beam,
passages must be cleared. The related whichever occurs later. Repeat
investigative and corrective actions, interval is not to exceed 10 years
if necessary, include a special after the last overhaul.
detailed inspection for corrosion
pits or damage of the beam, and
repair before further flight.
Group 1, Configuration 3 A general visual inspection (GVI) of Within 2 years after the date of this
airplanes with a MLG retract the beam is performed for damage, service bulletin. Repeat interval is
actuator beam having part number finish degradation, and corrosion. not to exceed 2 years after the last
(P/N) 65-46108-14 and previous The related investigative and inspection.
dash numbers that have not corrective actions, if necessary,
incorporated the original issue, include a special detailed inspection
Revision 1, or Revision 2 of the for corrosion pits or damage of the
service bulletin. beam, and repair before further
flight.
----------------------------------------------------------------------------------------------------------------
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously, except as discussed under
``Differences Between the Proposed AD and Service Information.''
Differences Between the Proposed AD and Service Information
Boeing Service Bulletin 737-32A1355, Revision 2, dated March 5,
2008, does not specify a compliance time for repairing the retract
actuator beam if damage, finish degradation, or corrosion is found.
This proposed AD would require that those repairs be done before
further flight after accomplishing the applicable inspections.
Boeing Service Bulletin 737-32A1355, Revision 2, dated March 5,
2008, specifies that the actions are for airplanes with new MLG retract
actuator beams having P/N 65-46108-15 and subsequent dash numbers that
have not been overhauled, and new or overhauled MLG retract actuator
beams having P/N 65-46108-14 and previous dash numbers. However, MLG
retract actuator beams which are not new or overhauled may also exhibit
the identified unsafe condition. For this reason, this proposed AD is
not limited to new or overhauled beams; the proposed AD would require
that the actions be done on airplanes having any MLG retract actuator
beam having one of those P/Ns. This correction will be included in the
next revision of the service bulletin.
We have coordinated these differences with the manufacturer.
Costs of Compliance
We estimate that this proposed AD would affect 652 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action/airplane group Work hours Average labor Parts cost Cost per product registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Overhaul for Group 1; Configurations 64 $80 None.................... $5,120, per overhaul 652 $3,338,240
1, 2, and 3. cycle.
Inspection for Group 1, Configuration 1 80 None.................... $80, per inspection 525 42,000
3. cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 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 this 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
[[Page 58908]]
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 FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2008-1070; Directorate Identifier 2008-NM-
087-AD.
Comments Due Date
(a) We must receive comments by November 24, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from reports of broken retract actuator
beams of the main landing gear (MLG) and the subsequent failure of
the MLG to fully retract. We are issuing this AD to detect and
correct broken retract actuator beams of the MLG, which could result
in damage to the beam arm, hydraulic tubing, and flight control
cables. Damage to the flight control cables could result in loss of
control of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Inspection and Related Investigative and Corrective Actions/Overhaul
(f) Except as provided by paragraphs (g) and (h) of this AD: At
the applicable times specified in paragraph 1.E. of Boeing Service
Bulletin 737-32A1355, Revision 2, dated March 5, 2008; inspect for
damage of the retract actuator beam of the MLG and overhaul the
retract actuator beam, as applicable, by doing all the applicable
actions specified in the Accomplishment Instructions of the service
bulletin. Do all applicable related investigative and corrective
actions before further flight. Repeat the applicable inspection or
overhaul thereafter at the applicable time specified in paragraph
1.E. of the service bulletin.
Exceptions to Service Information
(g) Where Boeing Service Bulletin 737-32A1355, Revision 2, dated
March 5, 2008, specifies a compliance time after ``* * * the date on
this service bulletin,'' this AD requires compliance within the
specified compliance time after the effective date of this AD.
(h) Boeing Service Bulletin 737-32A1355, Revision 2, dated March
5, 2008, specifies that the actions are for airplanes with new MLG
retract actuator beams that have not been overhauled having P/N 65-
46108-15 and subsequent dash numbers, and new or overhauled MLG
retract actuator beams having P/N 65-46108-14 and previous dash
numbers; however, this AD is not limited to new or overhauled beams.
This AD requires that the actions required by paragraph (f) of this
AD be done on airplanes with any MLG retract actuator beam having
those P/Ns.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM-
120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98057-3356; telephone (425) 917-6440; fax
(425) 917-6590; has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
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.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved the repair must meet the certification basis
of the airplane and the approval must specifically refer to this AD.
Issued in Renton, Washington, on September 26, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-23828 Filed 10-7-08; 8:45 am]
BILLING CODE 4910-13-P
