Airworthiness Directives; Boeing Model 737-300, -400, and -500 Series Airplanes, 65901-65903 [E7-22923]
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Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
65901
TABLE 2.—TERMINATING ACTIONS
Inspect—
(1) The elevator servo control to determine whether
part number (P/N)
SC4800–7A or –9 is installed.
(2) The elevator servo controls, P/N SC4800–10
and SC4800–11 to determine the serial number (S/N) installed.
In accordance with the accomplishment instructions
of airbus service bulletin—
A330–27–3128, dated May
3, 2005 (for Model
A330–200 and –300 series airplanes); or A340–
27–4129, dated May 3,
2005 (for Model A340–
200 and –300 series airplanes); as applicable.
None ..................................
And if—
Then—
P/N SC4800–7A or –9 is
found installed.
Modify the four elevator
servo controls.
The Accomplishment Instructions of the applicable Airbus service bulletin.
S/N 2324 or below is
found installed.
Replace the mode selector
valve position transducer
(MVT) of the elevator
servo controls with a
new MVT.
Paragraphs 3.(2) and
3.B.(2) of the Accomplishment Instructions of
Goodrich Actuation Systems Service Bulletin
SC4800–27–16, Revision 3, dated May 19,
2006.
Note 4: Airbus Service Bulletins A330–27–
3128 and A340–27–4129 refer to Goodrich
Actuation Systems Service Bulletin SC4800–
27–16, Revision 3, dated May 19, 2006, as an
additional source of service information for
accomplishing the modification of the four
elevator servo controls.
(n) Prior to or concurrently with the
replacement, if required, specified in
paragraph (m)(2) of this AD, replace the eyeend equipped with a self-lubricated bearing
with a new eye-end equipped with a roller
bearing, grease the new eye-end, and
reidentify the servo control, in accordance
with paragraph 2.A. of the Accomplishment
Instructions of TRW Service Bulletin
SC4800–27–34–09, Revision 1, dated
November 9, 2001.
(o) Accomplishing all of the applicable
actions required by paragraphs (m) and (n) of
this AD constitutes terminating action for
paragraphs (f) through (k) of this AD.
Issued in Renton, Washington, on
November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–22921 Filed 11–23–07; 8:45 am]
Alternative Methods of Compliance
(AMOCs)
AGENCY:
ebenthall on PROD1PC69 with PROPOSALS
(p)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) 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.
Related Information
(q) EASA airworthiness directive 2007–
0011, dated January 9, 2007, also addresses
the subject of this AD.
VerDate Aug<31>2005
15:37 Nov 23, 2007
Jkt 214001
In accordance with—
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0226; Directorate
Identifier 2007–NM–187–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–300, –400, and –500 Series
Airplanes
which could result in rapid
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by January 10, 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.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
Examining the AD Docket
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 737–300, –400,
and –500 series airplanes. This
proposed AD would require repetitive
inspections for cracking of the body
buttock line (BBL) 0.07 floor beam
between body station (BS) 651 and BS
676 and between BS 698 and BS 717,
and related investigative and corrective
actions if necessary. This AD also
provides an optional terminating action
for the repetitive inspections. This
proposed AD results from reports of
cracking in the BBL 0.07 floor beam. We
are proposing this AD to prevent failure
of the main deck floor beams at certain
body stations due to fatigue cracking,
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,
PO 00000
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65902
Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
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–2007–0226; Directorate Identifier
2007–NM–187–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.
ebenthall on PROD1PC69 with PROPOSALS
Other Related Rulemaking
On July 12, 2001, we issued AD 2001–
14–20, amendment 39–12331 (66 FR
38354, July 24, 2001), applicable to
certain Boeing Model 737–100 and –200
series airplanes. AD 2001–14–20
requires repetitive inspections to find
fatigue cracking in the main deck floor
beams located at certain body stations,
and repair if necessary. AD 2001–14–20
also provides for optional terminating
action for the repetitive inspections. AD
2001–14–20 addresses fatigue cracking
in the main deck floor beams on Model
737–100 and –200 series airplanes,
while this proposed AD would address
the same unsafe condition on Boeing
Model 737–300, –400, and –500 series
airplanes.
Discussion
Since we issued AD 2001–14–20,
several operators have reported cracking
in the body buttock line (BBL) 0.07 floor
beam on Model 737–300, –400, and
–500 series airplanes. The cracks were
similar to those found on the Model
737–100 and –200 series airplanes,
which are addressed by AD 2001–14–
20. Investigation revealed that the
cracks were caused by fatigue resulting
from pressurization flexure. Failure of
the main deck floor beam at certain
body stations due to fatigue cracking
could result in rapid decompression of
the airplane.
Relevant Service Information
We have reviewed Boeing Service
Bulletin 737–57–1210, Revision 2, dated
VerDate Aug<31>2005
15:37 Nov 23, 2007
Jkt 214001
June 13, 2007. For Model 737–300,
–400, and –500 series airplanes, the
service bulletin describes procedures for
accomplishing repetitive detailed
inspections for cracking of the BBL 0.07
floor beam between body station (BS)
651 and BS 676 and between BS 698
and BS 717, and doing related
investigative and corrective actions if
necessary. The related investigative
action includes doing a high frequency
eddy current (HFEC) inspection of the
fastener holes for cracking (1) prior to
modifying the floor beam, or (2) if any
cracking is found in the web (between
BS 651 and BS 676 and between BS 698
and BS 717) or in the upper chord
(between BS 651 and BS 676) during the
detailed inspection. The corrective
actions include the following:
• Repairing any cracking in
accordance with the service bulletin, if
cracking is found in the web (between
BS 651 and BS 676 and between BS 698
and BS 717) or in the upper chord
(between BS 651 and BS 676) during the
detailed inspection but no cracking is
found during the HFEC inspection.
Accomplishing the repair would
eliminate the need for the repetitive
inspections for the area in which the
repair is installed.
• Contacting Boeing for repair
instructions, (1) if cracking is found in
the web (between BS 651 and BS 676
and between BS 698 and BS 717) or in
the upper chord (between BS 651 and
BS 676) during the HFEC inspections,
(2) if cracking is found in the chords or
stiffeners (between BS 698 and BS 717)
or outside the typical crack locations
(between BS 651 and BS 676 and
between BS 698 and BS 717) during the
detailed inspection, or (3) if cracking is
found during the HFEC prior to
modifying the floor beam.
The service bulletin also provides
procedures for modifying the floor
beam, if no cracking is found during the
detailed and HFEC inspections.
Accomplishing the modification
(optional terminating action) would
eliminate the need for the repetitive
inspections for the area in which the
modification is installed.
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
PO 00000
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Fmt 4702
Sfmt 4702
the service information described
previously, except as discussed under
‘‘Difference Between the Proposed AD
and Service Bulletin.’’
Difference Between the Proposed AD
and Service Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions in
one of the following ways:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
Costs of Compliance
There are about 1,961 airplanes of the
affected design in the worldwide fleet.
This proposed AD would affect about
599 airplanes of U.S. registry. The
proposed inspections would take about
4 work hours per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
the proposed AD for U.S. operators is
$191,680, or $320 per airplane, per
inspection 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 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
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Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA–2007–0226;
Directorate Identifier 2007–NM–187–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by January 10, 2008.
Affected ADs
(b) None.
ebenthall on PROD1PC69 with PROPOSALS
Applicability
(c) This AD applies to Boeing Model 737–
300, –400, and –500 series airplanes,
certificated in any category; as identified in
Boeing Service Bulletin 737–57–1210,
excluding Appendix A, Revision 2, dated
June 13, 2007.
Unsafe Condition
(d) This AD results from reports of cracking
in the body buttock line (BBL) 0.07 floor
beam. We are issuing this AD to prevent
failure of the main deck floor beams at
certain body stations due to fatigue cracking,
which could result in rapid decompression of
the airplane.
VerDate Aug<31>2005
15:37 Nov 23, 2007
Jkt 214001
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.
Inspections and Related Investigative/
Corrective Actions
(f) Before the accumulation of 20,000 total
flight hours, or within 7,000 flight cycles
after the effective date of this AD, whichever
occurs later: Do the detailed inspections for
cracking of the BBL 0.07 floor beam between
body station (BS) 651 and BS 676 and
between BS 698 and BS 717, and do all the
applicable related investigative and
corrective actions before further flight, by
accomplishing all of the applicable actions
specified in paragraphs B.2. and B.4. of the
Accomplishment Instructions of Boeing
Service Bulletin 737–57–1210, excluding
Appendix A, Revision 2, dated June 13, 2007,
except as provided by paragraph (g) of this
AD. Repeat the inspections thereafter at
intervals not to exceed 7,000 flight cycles.
Installing a repair in accordance with
paragraphs B.2. and B.4. of the
Accomplishment Instructions of the service
bulletin, or doing the modification in
accordance with paragraph (h) of this AD,
terminates the repetitive inspections for the
applicable area only.
Exception to Corrective Action
(g) If any cracking is found during any
inspection required by this AD, and Boeing
Service Bulletin 737–57–1210, excluding
Appendix A, Revision 2, dated June 13, 2007,
specifies to contact Boeing for appropriate
action: Before further flight, repair the
cracking using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
Optional Terminating Action
(h) If no cracking is found during the
detailed inspection and related investigative
action required by paragraph (f) of this AD:
Accomplishing the modification of the BBL
0.07 floor beam between BS 651 and BS 676
and between BS 698 and BS 717, as
applicable, in accordance with paragraphs
B.2. and B.4., as applicable, of the
Accomplishment Instructions of Boeing
Service Bulletin 737–57–1210, excluding
Appendix A, Revision 2, dated June 13, 2007,
terminates the repetitive inspections for the
applicable area only.
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 in accordance with 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
PO 00000
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Fmt 4702
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65903
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
November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–22923 Filed 11–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0225; Directorate
Identifier 2007–NM–210–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757 Airplanes Equipped with
Rolls Royce RB211–535E Engines
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 Boeing Model 757 airplanes
equipped with Rolls Royce RB211–535E
engines. This proposed AD would
require repetitive inspections for signs
of damage of the aft hinge fittings and
attachment bolts of the thrust reversers,
and related investigative and corrective
actions if necessary. This proposed AD
results from reports of several incidents
of bolt failure at the aft hinge fittings of
the thrust reversers due to, among other
things, high operational loads. We are
proposing this AD to prevent failure of
the attachment bolts and consequent
separation of a thrust reverser from the
airplane during flight, which could
result in structural damage to the
airplane.
We must receive comments on
this proposed AD by January 10, 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
DATES:
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]]>Agencies
[Federal Register Volume 72, Number 226 (Monday, November 26, 2007)]
[Proposed Rules]
[Pages 65901-65903]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22923]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0226; Directorate Identifier 2007-NM-187-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-300, -400, and -500
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 Boeing Model 737-300, -400, and -500 series airplanes. This
proposed AD would require repetitive inspections for cracking of the
body buttock line (BBL) 0.07 floor beam between body station (BS) 651
and BS 676 and between BS 698 and BS 717, and related investigative and
corrective actions if necessary. This AD also provides an optional
terminating action for the repetitive inspections. This proposed AD
results from reports of cracking in the BBL 0.07 floor beam. We are
proposing this AD to prevent failure of the main deck floor beams at
certain body stations due to fatigue cracking, which could result in
rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by January 10,
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,
[[Page 65902]]
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-2007-0226;
Directorate Identifier 2007-NM-187-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.
Other Related Rulemaking
On July 12, 2001, we issued AD 2001-14-20, amendment 39-12331 (66
FR 38354, July 24, 2001), applicable to certain Boeing Model 737-100
and -200 series airplanes. AD 2001-14-20 requires repetitive
inspections to find fatigue cracking in the main deck floor beams
located at certain body stations, and repair if necessary. AD 2001-14-
20 also provides for optional terminating action for the repetitive
inspections. AD 2001-14-20 addresses fatigue cracking in the main deck
floor beams on Model 737-100 and -200 series airplanes, while this
proposed AD would address the same unsafe condition on Boeing Model
737-300, -400, and -500 series airplanes.
Discussion
Since we issued AD 2001-14-20, several operators have reported
cracking in the body buttock line (BBL) 0.07 floor beam on Model 737-
300, -400, and -500 series airplanes. The cracks were similar to those
found on the Model 737-100 and -200 series airplanes, which are
addressed by AD 2001-14-20. Investigation revealed that the cracks were
caused by fatigue resulting from pressurization flexure. Failure of the
main deck floor beam at certain body stations due to fatigue cracking
could result in rapid decompression of the airplane.
Relevant Service Information
We have reviewed Boeing Service Bulletin 737-57-1210, Revision 2,
dated June 13, 2007. For Model 737-300, -400, and -500 series
airplanes, the service bulletin describes procedures for accomplishing
repetitive detailed inspections for cracking of the BBL 0.07 floor beam
between body station (BS) 651 and BS 676 and between BS 698 and BS 717,
and doing related investigative and corrective actions if necessary.
The related investigative action includes doing a high frequency eddy
current (HFEC) inspection of the fastener holes for cracking (1) prior
to modifying the floor beam, or (2) if any cracking is found in the web
(between BS 651 and BS 676 and between BS 698 and BS 717) or in the
upper chord (between BS 651 and BS 676) during the detailed inspection.
The corrective actions include the following:
Repairing any cracking in accordance with the service
bulletin, if cracking is found in the web (between BS 651 and BS 676
and between BS 698 and BS 717) or in the upper chord (between BS 651
and BS 676) during the detailed inspection but no cracking is found
during the HFEC inspection. Accomplishing the repair would eliminate
the need for the repetitive inspections for the area in which the
repair is installed.
Contacting Boeing for repair instructions, (1) if cracking
is found in the web (between BS 651 and BS 676 and between BS 698 and
BS 717) or in the upper chord (between BS 651 and BS 676) during the
HFEC inspections, (2) if cracking is found in the chords or stiffeners
(between BS 698 and BS 717) or outside the typical crack locations
(between BS 651 and BS 676 and between BS 698 and BS 717) during the
detailed inspection, or (3) if cracking is found during the HFEC prior
to modifying the floor beam.
The service bulletin also provides procedures for modifying the
floor beam, if no cracking is found during the detailed and HFEC
inspections. Accomplishing the modification (optional terminating
action) would eliminate the need for the repetitive inspections for the
area in which the modification is installed.
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, except as discussed under
``Difference Between the Proposed AD and Service Bulletin.''
Difference Between the Proposed AD and Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Costs of Compliance
There are about 1,961 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 599 airplanes of
U.S. registry. The proposed inspections would take about 4 work hours
per airplane, at an average labor rate of $80 per work hour. Based on
these figures, the estimated cost of the proposed AD for U.S. operators
is $191,680, or $320 per airplane, per inspection 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 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
[[Page 65903]]
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):
Boeing: Docket No. FAA-2007-0226; Directorate Identifier 2007-NM-
187-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
10, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-300, -400, and -500
series airplanes, certificated in any category; as identified in
Boeing Service Bulletin 737-57-1210, excluding Appendix A, Revision
2, dated June 13, 2007.
Unsafe Condition
(d) This AD results from reports of cracking in the body buttock
line (BBL) 0.07 floor beam. We are issuing this AD to prevent
failure of the main deck floor beams at certain body stations due to
fatigue cracking, which could result in rapid decompression of the
airplane.
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.
Inspections and Related Investigative/Corrective Actions
(f) Before the accumulation of 20,000 total flight hours, or
within 7,000 flight cycles after the effective date of this AD,
whichever occurs later: Do the detailed inspections for cracking of
the BBL 0.07 floor beam between body station (BS) 651 and BS 676 and
between BS 698 and BS 717, and do all the applicable related
investigative and corrective actions before further flight, by
accomplishing all of the applicable actions specified in paragraphs
B.2. and B.4. of the Accomplishment Instructions of Boeing Service
Bulletin 737-57-1210, excluding Appendix A, Revision 2, dated June
13, 2007, except as provided by paragraph (g) of this AD. Repeat the
inspections thereafter at intervals not to exceed 7,000 flight
cycles. Installing a repair in accordance with paragraphs B.2. and
B.4. of the Accomplishment Instructions of the service bulletin, or
doing the modification in accordance with paragraph (h) of this AD,
terminates the repetitive inspections for the applicable area only.
Exception to Corrective Action
(g) If any cracking is found during any inspection required by
this AD, and Boeing Service Bulletin 737-57-1210, excluding Appendix
A, Revision 2, dated June 13, 2007, specifies to contact Boeing for
appropriate action: Before further flight, repair the cracking using
a method approved in accordance with the procedures specified in
paragraph (i) of this AD.
Optional Terminating Action
(h) If no cracking is found during the detailed inspection and
related investigative action required by paragraph (f) of this AD:
Accomplishing the modification of the BBL 0.07 floor beam between BS
651 and BS 676 and between BS 698 and BS 717, as applicable, in
accordance with paragraphs B.2. and B.4., as applicable, of the
Accomplishment Instructions of Boeing Service Bulletin 737-57-1210,
excluding Appendix A, Revision 2, dated June 13, 2007, terminates
the repetitive inspections for the applicable area only.
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 in
accordance with 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 November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-22923 Filed 11-23-07; 8:45 am]
BILLING CODE 4910-13-P
