Airworthiness Directives; Boeing Model 737-600, -700, and -800 Series Airplanes, 9776-9778 [E9-4732]
Download as PDF
<![CDATA[
9776
Federal Register / Vol. 74, No. 43 / Friday, March 6, 2009 / Proposed Rules
Compliance
Certain Requirement of AD 98–06–07
(i) Actions done before the effective date of
this AD in accordance with Fokker Service
Bulletin SBF100–76–014, dated October 1,
2001; or Revision 1, dated June 1, 2002; are
acceptable for compliance with the
requirements of paragraph (h) of this AD.
Airplane Flight Manual (AFM) Revision
AFM Revision
(g) Within 72 hours after March 27, 1998
(the effective date of AD 98–06–07), revise
the Limitations Section of the FAA-approved
AFM to add the following. This may be
accomplished by inserting a copy of this AD
in the AFM.
(j) Concurrently with the requirements of
paragraph (h) of this AD, revise the
Limitations Section of the Fokker F.28 Mark
0100 AFM to include the following (this may
be accomplished by inserting a copy of this
AD into the AFM):
‘‘LIMITATIONS POWERPLANT AND APU
LIMITATIONS
‘‘THRUST REVERSERS
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
OPERATING LIMITS
• To avoid high fan blade stresses,
stabilized operation in the speed range
between 60% and 75% Low Pressure
Rotational Speed (N1) is not permitted
during Ground Operations in Forward or
Reverse Thrust, except that passing through
this range while increasing or decreasing
thrust is permitted.
THRUST REVERSER
Thrust reversers are intended for ground
use only. Intentional use of reverse thrust in
flight is prohibited. After reverse thrust has
been initiated, a full stop landing must be
made.
Maximum Reverse Thrust Lever Positions
Normal Operation:
—The idle detent position shall not be
exceeded in normal operation.
—Momentarily exceeding the idle detent
position, while selecting idle reverse, is
acceptable.
Emergency Operation:
—In case of emergency, the emergency
maximum reverse thrust may be used.
—If directional control problems occur,
reduce to idle reverse or select forward
idle.
—Stabilized operation with the reverse lever
in an intermediate position between idle
reverse and emergency maximum reverse
is prohibited, except (where approved)
during Power-Back operations.’’
Note 1: Fokker Services Manual Change
Notification—Operational Documentation
(MCNO) No. F100–006, dated November 27,
1997, contains information that pertains to
this subject. Rolls-Royce PLC Engine
Operating Instruction Manual Reference F–
TAY–3RR, revised by transmittal letter No.
13, dated October 15, 1997, also pertains to
this subject.
mstockstill on PROD1PC66 with PROPOSALS
New Actions Required by This AD
Removal of Normal Maximum Detent
(h) Within 12 months after the effective
date of this AD, remove the normal
maximum (second) detent for the reversethrust control, in accordance with the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–76–014, Revision 2,
dated December 12, 2007. Accomplishing the
removal terminates the requirements of
paragraph (g) of this AD.
VerDate Nov<24>2008
16:17 Mar 05, 2009
Jkt 217001
Thrust reversers are intended for ground
use only. Intentional use of reverse thrust in
flight is prohibited.
The use of Max Reverse thrust is limited
to operations on short runways or on
runways with a reduced runway surface
friction coefficient or in emergency
conditions. Max Reverse thrust shall not be
used at airspeeds below 60 knots except in
emergency conditions.
Reverse thrust selections between Idle
Reverse thrust and Max Reverse thrust are
prohibited.’’
Note 2: Fokker Manual Change
Notification—Operational Documentation
(MCNO) F100–032, Revision 1, dated
September 21, 2007, contains information
related to the AFM revision required by
paragraph (j) of this AD.
Alternative Methods of Compliance
(AMOCs)
(k) 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: Tom Rodriguez,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1137; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
Related Information
(l) The European Aviation Safety Agency
Airworthiness Directive 2008–0089, dated
May 13, 2008, also addresses the subject of
this AD.
Issued in Renton, Washington, on February
20, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–4731 Filed 3–5–09; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0669; Directorate
Identifier 2007–NM–350–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, and –800 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
SUMMARY: We are revising an earlier
proposed airworthiness directive (AD)
for certain Boeing Model 737–600, –700,
and –800 series airplanes. The original
NPRM would have required an
inspection of the free flange of the lower
stringers of the wing center section for
drill starts, and applicable related
investigative and corrective actions. The
original NPRM resulted from drill starts
being found on the free flange of the
lower stringers of the wing center
section during a quality assurance
inspection at the final assembly plant.
This action revises the original NPRM
by expanding the inspection area to
include the free flange, the vertical web,
and the fillet radius between the vertical
web and the free flange. We are
proposing this supplemental NPRM to
prevent cracks from propagating from
drill starts in the free flange, vertical
web, and radius between the free flange
and vertical web of the lower stringers
of the wing center section lower
stringers, which could cause a loss of
structural integrity of the wing center
section and may result in a fuel leak.
DATES: We must receive comments on
this supplemental NPRM by March 31,
2009.
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.
E:\FR\FM\06MRP1.SGM
06MRP1
Federal Register / Vol. 74, No. 43 / Friday, March 6, 2009 / Proposed Rules
that would apply to certain Boeing
Model 737–600, –700, and –800 series
airplanes. That original NPRM was
published in the Federal Register on
June 24, 2008 (73 FR 35593). That
original NPRM proposed to require
inspecting the free flange of the lower
stringers of the wing center section for
drill starts, and applicable related
investigative and corrective actions.
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:
mstockstill on PROD1PC66 with PROPOSALS
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207;
telephone 206–544–9990; fax 206–766–
5682; e-mail DDCS@boeing.com;
Internet https://
www.myboeingfleet.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221
or 425–227–1152.
Request To Clarify Inspection
Requirements
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–2008–0669; Directorate Identifier
2007–NM–350–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 issued a notice of proposed
rulemaking (NPRM) (the ‘‘original
NPRM’’) to amend 14 CFR part 39 to
include an airworthiness directive (AD)
VerDate Nov<24>2008
16:17 Mar 05, 2009
Jkt 217001
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Boeing notes that the original NPRM
would have required an inspection of
the free flange of the stringer, whereas
paragraph 3.B.2. of the Accomplishment
Instructions in Boeing Alert Service
Bulletin 737–57A1294, dated April 23,
2007, calls for inspection as given in
Figure 1 of the service bulletin. Figure
1 specifies that the free flange, vertical
web, and radius between the free flange
and vertical web must be inspected.
(The original NPRM referred to this
service bulletin as the appropriate
source of service information for the
proposed actions.) The commenter
requests that we clarify whether the
inspection area is to include the free
flange, vertical web, and the fillet
radius.
We agree that the original NPRM is
unclear whether the inspection area
includes all three parts of the stringer.
The service bulletin does not
consistently include all three parts of
the stringer. The ‘‘Background’’ section,
the ‘‘Action’’ section, Paragraph 1.C.,
‘‘Reason,’’ Paragraph 1.D.,
‘‘Description,’’ and Paragraph 3.B.,
‘‘Work Instructions,’’ refer only to the
free flange for the inspection. Only a
note in Figure 1, Sheet 4, contains any
reference to all three areas of
inspection—free flange, vertical web,
and the fillet radius. We have
determined that all three areas must be
inspected to adequately address the
identified unsafe condition. We have
revised paragraph (g) of the
supplemental NRPM to explicitly state
these three areas of inspection. We have
also revised the description of the area
in the summary and paragraph (e) of the
supplemental NPRM.
Actions Since the Original NPRM Was
Issued
We have added a new paragraph (d)
to this proposed AD to specify the Air
Transport Association (ATA) of America
code identifying the subject, and re-
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
9777
identified the subsequent paragraphs
accordingly.
FAA’s Determination and Proposed
Requirements of the Supplemental
NPRM
We are proposing this supplemental
NPRM 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. The change
described above expands the scope of
the original NPRM. As a result, we have
determined that it is necessary to reopen
the comment period to provide
additional opportunity for the public to
comment on this supplemental NPRM.
Costs of Compliance
We estimate that this proposed AD
would affect 17 airplanes of U.S.
registry. We also estimate that it would
take 7 work-hours per product to
comply with this proposed AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this proposed AD to the U.S.
operators to be $9,520, or $560 per
product.
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:
E:\FR\FM\06MRP1.SGM
06MRP1
9778
Federal Register / Vol. 74, No. 43 / Friday, March 6, 2009 / Proposed Rules
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Applicability
(c) This AD applies to Boeing Model 737–
600, –700, and –800 series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 737–57A1294,
dated April 23, 2007.
AD, and Boeing Alert Service Bulletin 737–
57A1294, dated April 23, 2007, specifies to
contact Boeing for appropriate action: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Alternative Methods of Compliance
(AMOCs)
Unsafe Condition
(e) This AD results from drill starts being
found on the free flange of the lower stringers
of the wing center section during a quality
assurance inspection at the final assembly
plant. We are issuing this AD to prevent
cracks from propagating from drill starts in
the free flange, vertical web, and radius
between the free flange and vertical web of
the lower stringers of the wing center section
lower stringers, which could cause a loss of
structural integrity of the wing center section
and may result in a fuel leak.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
PART 39—AIRWORTHINESS
DIRECTIVES
Inspection and Related Investigative and
Corrective Actions
(g) Before the accumulation of 18,000 total
flight cycles, or within 90 days after the
effective date of this AD, whichever occurs
later, do a detailed inspection of the free
flange, vertical web, and radius between the
free flange and vertical web of the lower
stringers of the wing center section for any
drill start, and do all applicable related
investigative and corrective actions, by
accomplishing all the applicable actions
specified in paragraphs 3.B.2 and 3.B.4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–57A1294, dated April
23, 2007; except as provided in paragraph (h)
of this AD. The applicable related
investigative and corrective actions must be
done before further flight.
(h) If any crack is found during any
inspection required by paragraph (g) of this
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–2008–0669;
Directorate Identifier 2007–NM–350–AD.
Comments Due Date
(a) We must receive comments by March
31, 2009.
Affected ADs
mstockstill on PROD1PC66 with PROPOSALS
(b) None.
VerDate Nov<24>2008
16:17 Mar 05, 2009
Jkt 217001
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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:
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.
(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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 February
20, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–4732 Filed 3–5–09; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\06MRP1.SGM
06MRP1
]]>Agencies
[Federal Register Volume 74, Number 43 (Friday, March 6, 2009)]
[Proposed Rules]
[Pages 9776-9778]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-4732]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0669; Directorate Identifier 2007-NM-350-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, and -800
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for certain Boeing Model 737-600, -700, and -800 series airplanes.
The original NPRM would have required an inspection of the free flange
of the lower stringers of the wing center section for drill starts, and
applicable related investigative and corrective actions. The original
NPRM resulted from drill starts being found on the free flange of the
lower stringers of the wing center section during a quality assurance
inspection at the final assembly plant. This action revises the
original NPRM by expanding the inspection area to include the free
flange, the vertical web, and the fillet radius between the vertical
web and the free flange. We are proposing this supplemental NPRM to
prevent cracks from propagating from drill starts in the free flange,
vertical web, and radius between the free flange and vertical web of
the lower stringers of the wing center section lower stringers, which
could cause a loss of structural integrity of the wing center section
and may result in a fuel leak.
DATES: We must receive comments on this supplemental NPRM by March 31,
2009.
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.
[[Page 9777]]
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207; telephone 206-544-9990; fax 206-766-5682; e-mail DDCS@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221 or
425-227-1152.
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-2008-0669;
Directorate Identifier 2007-NM-350-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 issued a notice of proposed rulemaking (NPRM) (the ``original
NPRM'') to amend 14 CFR part 39 to include an airworthiness directive
(AD) that would apply to certain Boeing Model 737-600, -700, and -800
series airplanes. That original NPRM was published in the Federal
Register on June 24, 2008 (73 FR 35593). That original NPRM proposed to
require inspecting the free flange of the lower stringers of the wing
center section for drill starts, and applicable related investigative
and corrective actions.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Request To Clarify Inspection Requirements
Boeing notes that the original NPRM would have required an
inspection of the free flange of the stringer, whereas paragraph 3.B.2.
of the Accomplishment Instructions in Boeing Alert Service Bulletin
737-57A1294, dated April 23, 2007, calls for inspection as given in
Figure 1 of the service bulletin. Figure 1 specifies that the free
flange, vertical web, and radius between the free flange and vertical
web must be inspected. (The original NPRM referred to this service
bulletin as the appropriate source of service information for the
proposed actions.) The commenter requests that we clarify whether the
inspection area is to include the free flange, vertical web, and the
fillet radius.
We agree that the original NPRM is unclear whether the inspection
area includes all three parts of the stringer. The service bulletin
does not consistently include all three parts of the stringer. The
``Background'' section, the ``Action'' section, Paragraph 1.C.,
``Reason,'' Paragraph 1.D., ``Description,'' and Paragraph 3.B., ``Work
Instructions,'' refer only to the free flange for the inspection. Only
a note in Figure 1, Sheet 4, contains any reference to all three areas
of inspection--free flange, vertical web, and the fillet radius. We
have determined that all three areas must be inspected to adequately
address the identified unsafe condition. We have revised paragraph (g)
of the supplemental NRPM to explicitly state these three areas of
inspection. We have also revised the description of the area in the
summary and paragraph (e) of the supplemental NPRM.
Actions Since the Original NPRM Was Issued
We have added a new paragraph (d) to this proposed AD to specify
the Air Transport Association (ATA) of America code identifying the
subject, and re-identified the subsequent paragraphs accordingly.
FAA's Determination and Proposed Requirements of the Supplemental NPRM
We are proposing this supplemental NPRM 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.
The change described above expands the scope of the original NPRM. As a
result, we have determined that it is necessary to reopen the comment
period to provide additional opportunity for the public to comment on
this supplemental NPRM.
Costs of Compliance
We estimate that this proposed AD would affect 17 airplanes of U.S.
registry. We also estimate that it would take 7 work-hours per product
to comply with this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of this
proposed AD to the U.S. operators to be $9,520, or $560 per product.
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:
[[Page 9778]]
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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-2008-0669; Directorate Identifier 2007-NM-
350-AD.
Comments Due Date
(a) We must receive comments by March 31, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-600, -700, and -800
series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 737-57A1294, dated April 23, 2007.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Unsafe Condition
(e) This AD results from drill starts being found on the free
flange of the lower stringers of the wing center section during a
quality assurance inspection at the final assembly plant. We are
issuing this AD to prevent cracks from propagating from drill starts
in the free flange, vertical web, and radius between the free flange
and vertical web of the lower stringers of the wing center section
lower stringers, which could cause a loss of structural integrity of
the wing center section and may result in a fuel leak.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
Inspection and Related Investigative and Corrective Actions
(g) Before the accumulation of 18,000 total flight cycles, or
within 90 days after the effective date of this AD, whichever occurs
later, do a detailed inspection of the free flange, vertical web,
and radius between the free flange and vertical web of the lower
stringers of the wing center section for any drill start, and do all
applicable related investigative and corrective actions, by
accomplishing all the applicable actions specified in paragraphs
3.B.2 and 3.B.4 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-57A1294, dated April 23, 2007; except as
provided in paragraph (h) of this AD. The applicable related
investigative and corrective actions must be done before further
flight.
(h) If any crack is found during any inspection required by
paragraph (g) of this AD, and Boeing Alert Service Bulletin 737-
57A1294, dated April 23, 2007, specifies to contact Boeing for
appropriate action: Before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
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: 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.
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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 February 20, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-4732 Filed 3-5-09; 8:45 am]
BILLING CODE 4910-13-P
