Airworthiness Directives; Boeing Model 737-100, -200, and -200C Series Airplanes, 58005-58007 [05-19871]
Download as PDF
<![CDATA[
Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
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.
(4) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Material Incorporated by Reference
(l) You must use Boeing Alert Service
Bulletin 727–53A0227, dated September 16,
2004, to perform the actions that are required
by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19842 Filed 10–4–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21138; Directorate
Identifier 2004–NM–131–AD; Amendment
39–14310; AD 2005–20–16]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, and –200C Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–100, –200, and
–200C series airplanes. This AD requires
a one-time detailed inspection for
cracking of the lugs of the inboard
SUMMARY:
VerDate Aug<31>2005
14:00 Oct 04, 2005
Jkt 208001
58005
attach fittings of the wing leading edge
slat tracks at slat numbers 2 and 5; prior
or concurrent actions for certain
airplanes; repetitive high-frequency
eddy current (HFEC) inspections for
cracking of the lug surfaces of those
inboard attach fittings if necessary; and
replacement of the attach fittings with
new, improved fittings. This AD results
from reports of damage to the lugs of
certain inboard attach fittings of the
leading edge slat tracks. We are issuing
this AD to prevent a lifted slat, which,
if the airplane performs any non-normal
maneuver during takeoff or landing at
very high angles of attack, could lead to
the loss of the slat and reduced control
of the airplane.
DATES: This AD becomes effective
November 9, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 9, 2005.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
the wing leading edge slat tracks at slat
numbers 2 and 5; prior or concurrent
actions for certain airplanes; repetitive
high-frequency eddy current (HFEC)
inspections for cracking of the lug
surfaces of those inboard attach fittings
if necessary; and replacement of the
attach fittings with new, improved
fittings.
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
We have revised the ‘‘Alternative
Methods of Compliance (AMOCs)’’
paragraph in this AD to clarify the
delegation authority for Authorized
Representatives for the Boeing
Commercial Airplanes Delegation
Option Authorization.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Boeing Model 737–100,
–200, and –200C series airplanes. That
NPRM was published in the Federal
Register on May 9, 2005 (70 FR 24335).
That NPRM proposed to require a onetime detailed inspection for cracking of
the lugs of the inboard attach fittings of
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Support for the NPRM
One commenter, the manufacturer,
concurs with the content of the NPRM.
Request To Disallow Use of Aluminum
Attach Fittings
One commenter requests that we
revise the NPRM to prohibit replacing
aluminum attach fittings with new
aluminum fittings after the effective
date of the AD. The commenter provides
no justification for this request.
We do not agree with this request.
The manufacturer recommends that,
unless cracked, an aluminum attach
fitting need not be replaced until 120
months or 30,000 flight cycles,
whichever comes first, after the effective
date of the AD. We have determined
that the manufacturer recommendation
is sound and that the repetitive
inspections of the aluminum fittings
required by the AD are sufficient to
maintain safety until the aluminum
fittings are removed from service. We
have not changed the AD in this regard.
Explanation of Change Made to This
AD
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We have determined that these changes
E:\FR\FM\05OCR1.SGM
05OCR1
58006
Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
will neither increase the economic
burden on any operator nor increase the
scope of the AD.
Costs of Compliance
table provides the estimated costs for
U.S. operators to comply with this AD.
This AD will affect about 909
airplanes worldwide. The following
ESTIMATED COSTS
Work
hours
Average
labor rate
per hour
Detailed inspection ..........................................................
HFEC inspection ..............................................................
1
4
$65
65
None
None
Replace fitting ..................................................................
2
65
$1,674
Action
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 AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the National Government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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 AD and placed it in the AD docket.
VerDate Aug<31>2005
14:00 Oct 04, 2005
Jkt 208001
Parts
cost
Cost per
airplane
$65
$260, per inspection
cycle
$1,804
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, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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):
I
2005–20–16 Boeing: Amendment 39–14310.
Docket No. FAA–2005–21138;
Directorate Identifier 2004–NM–131–AD.
Effective Date
(a) This AD becomes effective November 9,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737–
100, –200, and –200C series airplanes; line
numbers 1 through 1585 inclusive;
certificated in any category.
Unsafe Condition
(d) This AD was prompted by reports of
damage to the lugs of certain inboard attach
fittings of the leading edge slat tracks. We are
issuing this AD to prevent a lifted slat,
which, if the airplane performs any nonnormal maneuver during takeoff or landing at
very high angles of attack, could lead to the
loss of the slat and reduced control of the
airplane.
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
Number of
U.S.-registered
airplanes
Fleet cost
522
522
$33,930.
$135,720, per inspection cycle.
522
$941,688.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–57–1273, Revision 2,
dated October 30, 2003; unless otherwise
specified in this AD.
Inspections
(g) Prior to the accumulation of 7,000 total
flight cycles or within 12 months after the
effective date of this AD, whichever occurs
later, perform a one-time detailed inspection
for cracking and damage of the inboard attach
fittings at slats 2 and 5 of the wing leading
edge in accordance with the service bulletin.
Note 1: For the purposes of this AD, a
detailed inspection is ‘‘An intensive visual
examination of a specific structural area,
system, installation, or assembly to detect
damage, failure, or irregularity. Available
lighting is normally supplemented with a
direct source of good lighting at intensity
deemed appropriate by the inspector.
Inspection aids such as mirror, magnifying
lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be
required.’’
(1) If any crack or damage is found, replace
the cracked inboard attach fitting in
accordance with paragraph (h) of this AD.
(2) If no crack or damage is found, within
4,500 flight cycles or 18 months after the
detailed inspection required by paragraph (g)
of this AD, whichever occurs first, perform a
high-frequency eddy current (HFEC)
inspection for cracking of the lugs of the
inboard attach fittings in accordance with the
service bulletin. If no crack is found, repeat
the HFEC inspection at intervals not to
exceed 4,500 flight cycles.
Replacement of Fittings
(h) Replace the aluminum inboard attach
fittings with new, improved steel fittings at
the applicable compliance time in paragraph
(h)(1) or (h)(2) of this AD in accordance with
the service bulletin. Replacement of any
aluminum fitting with a new, improved steel
fitting terminates the one-time detailed
inspection and the repetitive HFEC
E:\FR\FM\05OCR1.SGM
05OCR1
Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
inspections required by paragraph (g) of this
AD for that fitting.
(1) If any crack or damage is found during
any inspection required by paragraphs (g) or
(i) of this AD, before further flight.
(2) If no crack or damage is found during
any inspection required by paragraph (g) or
(i) of this AD, within 30,000 flight cycles or
within 120 months after the effective date of
this AD, whichever occurs first.
Concurrent Service Bulletin
(i) For airplanes listed in Group 2 of the
service bulletin: Prior to or during the onetime detailed inspection for cracking or
damage required by paragraph (g) of this AD
or during replacement of the fitting required
by paragraph (h) of this AD, whichever
occurs first, perform a detailed inspection on
slats 2 and 5 for interference of the slat tab
support clips with the slat track attach
fittings and trim the support clips to
eliminate any interference with the attach
fittings as applicable; in accordance with
Figure 3 of the Accomplishment Instructions
of Boeing Service Bulletin 737–57–1080,
Revision 3, dated September 24, 1992; and
replace any cracked or damaged aluminum
attach fitting with a new, improved steel
fitting in accordance with paragraph (h) of
this AD.
Actions Accomplished Per Previous Issue of
Service Bulletin
(j) Actions accomplished before the
effective date of this AD in accordance with
Boeing Service Bulletin 737–57–1080, dated
September 10, 1973; Revision 1, dated
February 25, 1983; or Revision 2, dated
August 24, 1989; are considered acceptable
for compliance with the corresponding
actions specified in paragraph (i) of this AD.
Alternative Methods of Compliance
(AMOCs)
(k)(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) 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 Airplane 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.
(3) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Material Incorporated by Reference
(l) You must use Boeing Special Attention
Service Bulletin 737–57–1273, Revision 2,
dated October 30, 2003; and Boeing Service
Bulletin 737–57–1080, Revision 3, dated
September 24, 1992; as applicable; to perform
the actions that are required by this AD,
unless the AD specifies otherwise. The
Director of the Federal Register approved the
VerDate Aug<31>2005
14:00 Oct 04, 2005
Jkt 208001
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207, for a copy
of this service information. You may review
copies at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on
September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19871 Filed 10–4–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20874; Directorate
Identifier 2004–NM–279–AD; Amendment
39–14311; AD 2005–20–17]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319–100 Series Airplanes; Model
A320–111 Series Airplanes; Model
A320–200 Series Airplanes; and Model
A321–100 and –200 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus airplane models, as specified
above. This AD requires modifying the
parking brake system to automatically
restore the normal brake if the parking
brake pressure decreases below a certain
threshold. This AD results from a report
of failure of the parking brake while the
airplane was on the holding point of the
runway before takeoff, leading to a
runway departure. We are issuing this
AD to ensure normal braking is
available to prevent possible runway
departure in the event of failure of the
parking brake.
DATES: This AD becomes effective
November 9, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 9, 2005.
ADDRESSES: You may examine the AD
docket on the Internet at https://
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
58007
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2141;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Airbus Model A319,
A320, and A321 series airplanes. That
NPRM was published in the Federal
Register on April 6, 2005 (70 FR 17351).
That NPRM proposed to require
modifying the parking brake system to
automatically restore the normal
parking brake if the parking brake
pressure decreases below a certain
threshold.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Support for the NPRM
Two commenters support the actions
required by the NPRM.
Request To Cite Latest Service
Information
One commenter asks that we change
the NPRM to refer to the latest revision
of Airbus Service Bulletin A320–32–
1201, which is Revision 02, dated
February 1, 2005. Airbus Service
Bulletin A320–32–1201, Revision 01,
dated May 29, 2002, was referenced in
the NPRM as the appropriate source of
service information for accomplishing
the specified modification. The
commenter states that Revision 02
E:\FR\FM\05OCR1.SGM
05OCR1
]]>Agencies
[Federal Register Volume 70, Number 192 (Wednesday, October 5, 2005)]
[Rules and Regulations]
[Pages 58005-58007]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19871]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21138; Directorate Identifier 2004-NM-131-AD;
Amendment 39-14310; AD 2005-20-16]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, and -200C
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 737-100, -200, and -200C series airplanes. This AD
requires a one-time detailed inspection for cracking of the lugs of the
inboard attach fittings of the wing leading edge slat tracks at slat
numbers 2 and 5; prior or concurrent actions for certain airplanes;
repetitive high-frequency eddy current (HFEC) inspections for cracking
of the lug surfaces of those inboard attach fittings if necessary; and
replacement of the attach fittings with new, improved fittings. This AD
results from reports of damage to the lugs of certain inboard attach
fittings of the leading edge slat tracks. We are issuing this AD to
prevent a lifted slat, which, if the airplane performs any non-normal
maneuver during takeoff or landing at very high angles of attack, could
lead to the loss of the slat and reduced control of the airplane.
DATES: This AD becomes effective November 9, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of November 9,
2005.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6440; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Boeing Model
737-100, -200, and -200C series airplanes. That NPRM was published in
the Federal Register on May 9, 2005 (70 FR 24335). That NPRM proposed
to require a one-time detailed inspection for cracking of the lugs of
the inboard attach fittings of the wing leading edge slat tracks at
slat numbers 2 and 5; prior or concurrent actions for certain
airplanes; repetitive high-frequency eddy current (HFEC) inspections
for cracking of the lug surfaces of those inboard attach fittings if
necessary; and replacement of the attach fittings with new, improved
fittings.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Support for the NPRM
One commenter, the manufacturer, concurs with the content of the
NPRM.
Request To Disallow Use of Aluminum Attach Fittings
One commenter requests that we revise the NPRM to prohibit
replacing aluminum attach fittings with new aluminum fittings after the
effective date of the AD. The commenter provides no justification for
this request.
We do not agree with this request. The manufacturer recommends
that, unless cracked, an aluminum attach fitting need not be replaced
until 120 months or 30,000 flight cycles, whichever comes first, after
the effective date of the AD. We have determined that the manufacturer
recommendation is sound and that the repetitive inspections of the
aluminum fittings required by the AD are sufficient to maintain safety
until the aluminum fittings are removed from service. We have not
changed the AD in this regard.
Explanation of Change Made to This AD
We have revised the ``Alternative Methods of Compliance (AMOCs)''
paragraph in this AD to clarify the delegation authority for Authorized
Representatives for the Boeing Commercial Airplanes Delegation Option
Authorization.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes
[[Page 58006]]
will neither increase the economic burden on any operator nor increase
the scope of the AD.
Costs of Compliance
This AD will affect about 909 airplanes worldwide. The following
table provides the estimated costs for U.S. operators to comply with
this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average Number of
Work labor U.S.-
Action hours rate per Parts cost Cost per airplane registered Fleet cost
hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed inspection................. 1 $65 None $65 522 $33,930.
HFEC inspection..................... 4 65 None $260, per inspection cycle 522 $135,720, per inspection cycle.
Replace fitting..................... 2 65 $1,674 $1,804 522 $941,688.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the National Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-20-16 Boeing: Amendment 39-14310. Docket No. FAA-2005-21138;
Directorate Identifier 2004-NM-131-AD.
Effective Date
(a) This AD becomes effective November 9, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-100, -200, and -200C
series airplanes; line numbers 1 through 1585 inclusive;
certificated in any category.
Unsafe Condition
(d) This AD was prompted by reports of damage to the lugs of
certain inboard attach fittings of the leading edge slat tracks. We
are issuing this AD to prevent a lifted slat, which, if the airplane
performs any non-normal maneuver during takeoff or landing at very
high angles of attack, could lead to the loss of the slat and
reduced control 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.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-57-1273, Revision 2, dated October 30, 2003; unless
otherwise specified in this AD.
Inspections
(g) Prior to the accumulation of 7,000 total flight cycles or
within 12 months after the effective date of this AD, whichever
occurs later, perform a one-time detailed inspection for cracking
and damage of the inboard attach fittings at slats 2 and 5 of the
wing leading edge in accordance with the service bulletin.
Note 1: For the purposes of this AD, a detailed inspection is
``An intensive visual examination of a specific structural area,
system, installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a
direct source of good lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror, magnifying lenses,
etc., may be used. Surface cleaning and elaborate access procedures
may be required.''
(1) If any crack or damage is found, replace the cracked inboard
attach fitting in accordance with paragraph (h) of this AD.
(2) If no crack or damage is found, within 4,500 flight cycles
or 18 months after the detailed inspection required by paragraph (g)
of this AD, whichever occurs first, perform a high-frequency eddy
current (HFEC) inspection for cracking of the lugs of the inboard
attach fittings in accordance with the service bulletin. If no crack
is found, repeat the HFEC inspection at intervals not to exceed
4,500 flight cycles.
Replacement of Fittings
(h) Replace the aluminum inboard attach fittings with new,
improved steel fittings at the applicable compliance time in
paragraph (h)(1) or (h)(2) of this AD in accordance with the service
bulletin. Replacement of any aluminum fitting with a new, improved
steel fitting terminates the one-time detailed inspection and the
repetitive HFEC
[[Page 58007]]
inspections required by paragraph (g) of this AD for that fitting.
(1) If any crack or damage is found during any inspection
required by paragraphs (g) or (i) of this AD, before further flight.
(2) If no crack or damage is found during any inspection
required by paragraph (g) or (i) of this AD, within 30,000 flight
cycles or within 120 months after the effective date of this AD,
whichever occurs first.
Concurrent Service Bulletin
(i) For airplanes listed in Group 2 of the service bulletin:
Prior to or during the one-time detailed inspection for cracking or
damage required by paragraph (g) of this AD or during replacement of
the fitting required by paragraph (h) of this AD, whichever occurs
first, perform a detailed inspection on slats 2 and 5 for
interference of the slat tab support clips with the slat track
attach fittings and trim the support clips to eliminate any
interference with the attach fittings as applicable; in accordance
with Figure 3 of the Accomplishment Instructions of Boeing Service
Bulletin 737-57-1080, Revision 3, dated September 24, 1992; and
replace any cracked or damaged aluminum attach fitting with a new,
improved steel fitting in accordance with paragraph (h) of this AD.
Actions Accomplished Per Previous Issue of Service Bulletin
(j) Actions accomplished before the effective date of this AD in
accordance with Boeing Service Bulletin 737-57-1080, dated September
10, 1973; Revision 1, dated February 25, 1983; or Revision 2, dated
August 24, 1989; are considered acceptable for compliance with the
corresponding actions specified in paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(k)(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) 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 Airplane
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.
(3) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Material Incorporated by Reference
(l) You must use Boeing Special Attention Service Bulletin 737-
57-1273, Revision 2, dated October 30, 2003; and Boeing Service
Bulletin 737-57-1080, Revision 3, dated September 24, 1992; as
applicable; to perform the actions that are required by this AD,
unless the AD specifies otherwise. The Director of the Federal
Register approved the incorporation by reference of these documents
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207,
for a copy of this service information. You may review copies at the
Docket Management Facility, U.S. Department of Transportation, 400
Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on
the Internet at https://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-19871 Filed 10-4-05; 8:45 am]
BILLING CODE 4910-13-P
