Airworthiness Directives; Boeing Model 737-100, -200, and -200C Series Airplanes, 36829-36831 [05-12503]
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Federal Register / Vol. 70, No. 122 / Monday, June 27, 2005 / Rules and Regulations
this AD, perform a one-time inspection and
records check to determine the weight of
equipment installed in that electrical rack.
This records review and inspection must
include determining what, if any, extra
equipment has been installed in the subject
racks of the airplane, performing a detailed
inspection to determine that this equipment
is installed on the airplane, calculating the
total weight of the installed equipment, and
comparing that total to the weight limit
specified on the placard installed per
paragraph (d)(2) of this AD. If the weight is
outside the limits specified in the placard,
before further flight, remove equipment from
the rack to meet the weight limit specified in
the placard.
(i) For airplanes on which the actions
required by paragraphs (d)(1) and (d)(2) of
this AD were done before the effective date
of this AD: Within 12 months after the
effective date of this AD.
(ii) For airplanes on which the actions
required by paragraphs (d)(1) and (d)(2) of
this AD are done after the effective date of
this AD: Before further flight after installing
the placards.
Actions Accomplished Previously
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the
Manager, Seattle Aircraft Certification Office,
FAA, is authorized to approve alternative
methods of compliance (AMOCs) for this AD.
Incorporation by Reference
(g) Unless otherwise specified in this AD,
the actions must be done in accordance with
Boeing Special Attention Service Bulletin
777–25–0144, Revision 2, dated January 15,
2004. This incorporation by reference was
approved by the Director of the Federal
Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. To get copies of this
service information, go to Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207. To inspect copies
of this service information, go to the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or to 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.
16:46 Jun 24, 2005
Jkt 205001
Issued in Renton, Washington, on June 15,
2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–12510 Filed 6–24–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002–NM–289–AD; Amendment
39–14167; AD 2005–13–30]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, -200, and -200C Series
Airplanes
Federal Aviation
Administration, Department of
Transportation.
ACTION: Final rule.
AGENCY:
(e) Actions accomplished before the
effective date of this AD per the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–25–
0144, dated January 25, 2001; or Revision 1,
dated January 10, 2002; are acceptable for
compliance with the corresponding actions
required by this AD, provided that the
additional actions specified in Part 2 or 3 of
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–25–
0144, Revision 2, dated January 15, 2004, are
accomplished within the compliance time
specified in this AD. The weighing
requirements in paragraphs (a)(2) and (d)(3)
of this AD must be accomplished at the
applicable times identified in those
paragraphs.
VerDate jul<14>2003
Effective Date
(h) This amendment becomes effective on
August 1, 2005.
This amendment adopts a
new airworthiness directive (AD),
applicable to all Boeing Model 737–100,
-200, and -200C series airplanes, that
requires repetitive inspections to detect
discrepancies of certain fuselage skin
panels located just aft of the wheel well,
and repair if necessary. The actions
specified by this AD are intended to
detect and correct fatigue cracking of the
skin panels, which could cause rapid
decompression of the airplane. This
action is intended to address the
identified unsafe condition.
DATES: Effective August 1, 2005.
The incorporation by reference of a
certain publication listed in the
regulations is approved by the Director
of the Federal Register as of August 1,
2005.
ADDRESSES: The service information
referenced in this AD may be obtained
from Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington
98124–2207. This information may be
examined at the Federal Aviation
Administration (FAA), Transport
Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW., Renton,
Washington.
SUMMARY:
FOR FURTHER INFORMATION CONTACT:
Suzanne Lucier, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6438; fax (425) 917–6590.
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36829
A
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an airworthiness directive (AD)
that is applicable to all Boeing Model
737–100, -200, and -200C series
airplanes was published as a
supplemental notice of proposed
rulemaking (NPRM) in the Federal
Register on April 1, 2005 (70 FR 16761).
SUPPLEMENTARY INFORMATION:
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that has been
submitted on the proposed AD.
Support for the Proposed AD
The commenter supports the
proposed AD.
Conclusion
We have carefully reviewed the
available data, including the comment
that has been submitted, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Interim Action
This is considered to be interim
action. The manufacturer has advised
that it is developing an improved
preventive modification intended to
address the identified unsafe condition
for unmodified skin areas. After this
modification is developed, approved,
and available, we may consider
additional rulemaking.
Cost Impact
There are about 1,000 airplanes of the
affected design in the worldwide fleet.
The FAA estimates that 390 airplanes of
U.S. registry will be affected by this AD.
The inspection will take about 47 to
88 work hours per airplane (depending
on configuration), at an average labor
rate of $65 per work hour. Based on
these figures, we estimate the cost of the
inspection to be $3,055 to $5,720 per
airplane, per inspection cycle.
The cost impact figure discussed
above is based on assumptions that no
operator has yet accomplished any of
the requirements of this AD action, and
that no operator would accomplish
those actions in the future if this AD
were not adopted. The cost impact
figures discussed in AD rulemaking
actions represent only the time
necessary to perform the specific actions
actually required by the AD. These
figures typically do not include
incidental costs, such as the time
required to gain access and close up,
planning time, or time necessitated by
other administrative actions.
E:\FR\FM\27JNR1.SGM
27JNR1
36830
Federal Register / Vol. 70, No. 122 / Monday, June 27, 2005 / Rules and Regulations
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 Impact
The regulations adopted herein 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. Therefore, it is
determined that this final rule does not
have federalism implications under
Executive Order 13132.
For the reasons discussed above, I
certify that this action (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. A final evaluation has
been prepared for this action and it is
contained in the Rules Docket. A copy
of it may be obtained from the Rules
Docket at the location provided under
the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
VerDate jul<14>2003
16:46 Jun 24, 2005
Jkt 205001
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. Section 39.13 is amended by adding
the following new airworthiness
directive:
I
2005–13–30 Boeing: Amendment 39–14167.
Docket 2002–NM–289–AD.
Applicability: All Model 737–100, -200,
and -200C series airplanes; certificated in any
category.
Compliance: Required as indicated, unless
accomplished previously.
To detect and correct fatigue cracking of
the skin panels, which could cause rapid
decompression of the airplane, accomplish
the following:
Repetitive Inspections: Unmodified Skin
Areas
(a) For fuselage skin panel areas that have
not been modified with stiffening angles:
Before the airplane accumulates 16,000 total
flight cycles, or within 4,500 flight cycles
after the effective date of this AD, whichever
occurs later, inspect the unmodified fuselage
side skins just aft of the main wheelwell, and
perform all follow-on actions, in accordance
with Part I of the Accomplishment
Instructions of Boeing Service Bulletin 737–
53–1065, Revision 2, dated April 19, 2001;
except as provided by paragraph (g) of this
AD. If no cracking, loose fasteners,
disbonding, or damage is found: Repeat the
inspection at the time specified in paragraph
1.E., Compliance, of the service bulletin, as
applicable, except as provided by paragraph
(d) of this AD.
Repetitive Inspections: Modified Skin Areas
(b) For fuselage skin panel areas that have
been modified with stiffening angles in
accordance with Boeing Service Bulletin
737–53–1065, dated January 4, 1985;
Revision 1, dated October 12, 1989; or
Revision 2, dated April 19, 2001: Before the
airplane accumulates 16,000 total flight
cycles, or within 4,500 flight cycles after the
effective date of this AD, whichever occurs
later, inspect the modified areas as specified
in accordance with Part I of Boeing Service
Bulletin 737–53–1065, Revision 2, dated
April 19, 2001. Repeat the inspection at the
time specified in paragraph 1.E., of the
service bulletin, as applicable, except as
provided by paragraph (d) of this AD. If any
cracks, loose fasteners, disbonding, or
damage is found: Repair before further flight
in accordance with the requirements of
paragraph (d) of this AD.
Terminating Action for Inspections of
Modified Skin Areas
(c) For fuselage skin panel areas that have
been modified with stiffening angles in
accordance with Boeing Service Bulletin
737–53–1065, dated January 4, 1985;
Revision 1, dated October 12, 1989; or
Revision 2, dated April 19, 2001: At the later
of the times specified by paragraphs (c)(1)
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and (c)(2) of this AD, perform a subsurface
eddy current or magneto optical imaging
inspection to detect subsurface skin cracks
along the edge of the bonded doubler, in
accordance with Figure 10 of Boeing Service
Bulletin 737–53–1065, Revision 2, dated
April 19, 2001; except as provided by
paragraph (g) of this AD. If any cracks are
found, repair before further flight in
accordance with paragraph (d) of this AD.
Accomplishment of this inspection and all
applicable corrective actions terminates the
repetitive inspections required by paragraph
(b) of this AD for the modified areas.
(1) Inspect within 24,500, but not fewer
than 20,000, flight cycles after the
modification of the skin.
(2) Inspect within 4,500 flight cycles after
the effective date of this AD.
Repair: Modified and Unmodified Skin
Areas
(d) If any cracking is detected during any
inspection required by this AD: Do the
actions specified by paragraph (d)(1) or (d)(2)
of this AD before further flight. Do the
actions in accordance with Boeing Service
Bulletin 737–53–1065, Revision 2, dated
April 19, 2001, except as required by
paragraph (e) of this AD.
(1) Do a time-limited repair (including a
detailed inspection of the skin in the area of
the repair to detect corrosion and doubler
disbonding) in accordance with Part III of the
Accomplishment Instructions of the service
bulletin.
(i) After the time-limited repair has been
accomplished: At intervals not to exceed
3,000 flight cycles, perform an external
general visual inspection of the repair to
detect loose or missing fasteners, in
accordance with Part III of the
Accomplishment Instructions of the service
bulletin, until the actions specified in
paragraph (d)(1)(v) of this AD have been
accomplished.
(ii) Within 4,500 flight cycles after the
time-limited repair has been accomplished:
Perform an internal inspection of the repair
to detect cracking or doubler disbonding
using general visual and high-frequency eddy
current methods, in accordance with Figure
11 of the service bulletin, unless the actions
specified in paragraph (d)(1)(v) of this AD
have been accomplished.
(iii) If any cracking is found during any
inspection required by paragraph (d)(1) of
this AD: Repair before further flight in
accordance with paragraph (e) of this AD.
Another approved repair method is in
Section 53–30–3, Figure 48, of the Boeing
737 Structural Repair Manual (SRM).
(iv) If any disbonding is found during any
inspection required by paragraph (d)(1) of
this AD: Repair before further flight in
accordance with Part II of the service
bulletin.
(v) Within 10,000 flight cycles after
accomplishment of the time-limited repair:
Make the repair permanent in accordance
with Part III of the Accomplishment
Instructions of the service bulletin.
Permanent repair of an area terminates the
repetitive inspections specified in this AD for
that repaired area only.
(2) Do a permanent repair (including an
inspection using external subsurface eddy
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Federal Register / Vol. 70, No. 122 / Monday, June 27, 2005 / Rules and Regulations
current or magneto optical imaging methods
to detect cracks at the chem-milled step in
each adjacent bay of the fuselage skin, a
detailed inspection of the skin in the area of
the repair for corrosion and doubler
disbonding, and applicable corrective action)
of the cracked area, in accordance with Part
II of the Accomplishment Instructions of the
service bulletin. Another approved repair
method is in Section 53–30–3, Figure 48, of
the Boeing 737 SRM. Permanent repair of an
area terminates the repetitive inspections
specified in this AD for that repaired area
only.
Exceptions to Service Bulletin Procedures
(e) During any inspection required by this
AD, if any discrepancy (including cracking)
is detected for which the service bulletin
specifies to contact Boeing for appropriation
action: Before further flight, repair according
to a method approved by the Manager,
Seattle Aircraft Certification Office (ACO),
FAA; or according to data meeting the
certification basis of the airplane approved
by an Authorized Representative for the
Boeing 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.
(f) Although Boeing Service Bulletin 737–
53–1065, Revision 2, dated April 19, 2001,
recommends that cracks found in Zone 2 be
reported to Boeing, this AD does not require
such a report.
(g) For airplanes subject to the
requirements of paragraphs (a) and (c) of this
AD: Inspections are not required in areas that
are spanned by an FAA-approved repair that
has a minimum of 3 rows of fasteners above
and below the chemical-milled step. If an
external doubler covers the chemical-milled
step, but does not span it by a minimum of
3 rows of fasteners above and below, one
method of compliance with the inspection
requirement of paragraphs (a) and (c) of this
AD is to inspect all chemical-milled steps
covered by the repair using internal
nondestructive test (NDT) methods in
accordance with Part 6, Subject 53–30–20, of
the Boeing 737 NDT Manual. Follow-on and
corrective actions must be done as specified
in this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) In accordance with 14 CFR 39.19, the
Manager, Seattle ACO, FAA, is authorized to
approve AMOCs for this AD.
(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
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.
Incorporation by Reference
(i) Unless otherwise specified in this AD,
the actions must be done in accordance with
VerDate jul<14>2003
16:46 Jun 24, 2005
Jkt 205001
Boeing Service Bulletin 737–53–1065,
Revision 2, dated April 19, 2001. This
incorporation by reference was approved by
the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get copies of this service
information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207. To inspect copies
of this service information, go to the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or to 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.
Effective Date
(j) This amendment becomes effective on
August 1, 2005.
Issued in Renton, Washington, on June 14,
2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–12503 Filed 6–24–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20871; Directorate
Identifier 2004–NM–212–AD; Amendment
39–14169; AD 2005–13–32]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 1000, 2000, 3000, and
4000 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Fokker Model F.28 Mark 1000, 2000,
3000, and 4000 airplanes. This AD
requires a detailed inspection to
determine the presence of incorrectly
installed bushings in the attachment
holes of the reinforcing strap of the leftand right-hand wings’ lower skin, and
corrective actions if necessary. This AD
is prompted by a report that bushings
were installed in accordance with
improper procedures in the structural
repair manual. We are issuing this AD
to detect and correct improperly
installed bushings, which could result
in reduced tensile strength of the
reinforcing strap of the wing’s lower
skin, and consequently a reduction of
the structural capability of the wing and
possible wing failure.
PO 00000
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36831
This AD becomes effective
August 1, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of August 1, 2005.
ADDRESSES: For service information
identified in this AD, contact Fokker
Services B.V., P.O. Box 231, 2150 AE
Nieuw-Vennep, the Netherlands.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20871; the directorate
identifier for this docket is 2004-NM–
212-AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for all Fokker Model F.28 Mark
1000, 2000, 3000, and 4000 airplanes.
That action, published in the Federal
Register on April 6, 2005 (70 FR 17345),
proposed to require a detailed
inspection to determine the presence of
incorrectly installed bushings in the
attachment holes of the reinforcing strap
of the left- and right-hand wings’ lower
skin, and corrective actions if necessary.
DATES:
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been submitted on the proposed
AD or on the determination of the cost
to the public.
Explanation of Change to Applicability
We have revised the applicability of
the proposed AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
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]]>Agencies
[Federal Register Volume 70, Number 122 (Monday, June 27, 2005)]
[Rules and Regulations]
[Pages 36829-36831]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12503]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-289-AD; Amendment 39-14167; AD 2005-13-30]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-100, -200, and -200C
Series Airplanes
AGENCY: Federal Aviation Administration, Department of Transportation.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Boeing Model 737-100, -200, and -200C series
airplanes, that requires repetitive inspections to detect discrepancies
of certain fuselage skin panels located just aft of the wheel well, and
repair if necessary. The actions specified by this AD are intended to
detect and correct fatigue cracking of the skin panels, which could
cause rapid decompression of the airplane. This action is intended to
address the identified unsafe condition.
DATES: Effective August 1, 2005.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of August 1, 2005.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6438; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to all Boeing Model 737-100, -200,
and -200C series airplanes was published as a supplemental notice of
proposed rulemaking (NPRM) in the Federal Register on April 1, 2005 (70
FR 16761).
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
submitted on the proposed AD.
Support for the Proposed AD
The commenter supports the proposed AD.
Conclusion
We have carefully reviewed the available data, including the
comment that has been submitted, and determined that air safety and the
public interest require adopting the AD as proposed.
Interim Action
This is considered to be interim action. The manufacturer has
advised that it is developing an improved preventive modification
intended to address the identified unsafe condition for unmodified skin
areas. After this modification is developed, approved, and available,
we may consider additional rulemaking.
Cost Impact
There are about 1,000 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 390 airplanes of U.S. registry
will be affected by this AD.
The inspection will take about 47 to 88 work hours per airplane
(depending on configuration), at an average labor rate of $65 per work
hour. Based on these figures, we estimate the cost of the inspection to
be $3,055 to $5,720 per airplane, per inspection cycle.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the requirements of this AD
action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
[[Page 36830]]
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 Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness
directive:
2005-13-30 Boeing: Amendment 39-14167. Docket 2002-NM-289-AD.
Applicability: All Model 737-100, -200, and -200C series
airplanes; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracking of the skin panels, which
could cause rapid decompression of the airplane, accomplish the
following:
Repetitive Inspections: Unmodified Skin Areas
(a) For fuselage skin panel areas that have not been modified
with stiffening angles: Before the airplane accumulates 16,000 total
flight cycles, or within 4,500 flight cycles after the effective
date of this AD, whichever occurs later, inspect the unmodified
fuselage side skins just aft of the main wheelwell, and perform all
follow-on actions, in accordance with Part I of the Accomplishment
Instructions of Boeing Service Bulletin 737-53-1065, Revision 2,
dated April 19, 2001; except as provided by paragraph (g) of this
AD. If no cracking, loose fasteners, disbonding, or damage is found:
Repeat the inspection at the time specified in paragraph 1.E.,
Compliance, of the service bulletin, as applicable, except as
provided by paragraph (d) of this AD.
Repetitive Inspections: Modified Skin Areas
(b) For fuselage skin panel areas that have been modified with
stiffening angles in accordance with Boeing Service Bulletin 737-53-
1065, dated January 4, 1985; Revision 1, dated October 12, 1989; or
Revision 2, dated April 19, 2001: Before the airplane accumulates
16,000 total flight cycles, or within 4,500 flight cycles after the
effective date of this AD, whichever occurs later, inspect the
modified areas as specified in accordance with Part I of Boeing
Service Bulletin 737-53-1065, Revision 2, dated April 19, 2001.
Repeat the inspection at the time specified in paragraph 1.E., of
the service bulletin, as applicable, except as provided by paragraph
(d) of this AD. If any cracks, loose fasteners, disbonding, or
damage is found: Repair before further flight in accordance with the
requirements of paragraph (d) of this AD.
Terminating Action for Inspections of Modified Skin Areas
(c) For fuselage skin panel areas that have been modified with
stiffening angles in accordance with Boeing Service Bulletin 737-53-
1065, dated January 4, 1985; Revision 1, dated October 12, 1989; or
Revision 2, dated April 19, 2001: At the later of the times
specified by paragraphs (c)(1) and (c)(2) of this AD, perform a
subsurface eddy current or magneto optical imaging inspection to
detect subsurface skin cracks along the edge of the bonded doubler,
in accordance with Figure 10 of Boeing Service Bulletin 737-53-1065,
Revision 2, dated April 19, 2001; except as provided by paragraph
(g) of this AD. If any cracks are found, repair before further
flight in accordance with paragraph (d) of this AD. Accomplishment
of this inspection and all applicable corrective actions terminates
the repetitive inspections required by paragraph (b) of this AD for
the modified areas.
(1) Inspect within 24,500, but not fewer than 20,000, flight
cycles after the modification of the skin.
(2) Inspect within 4,500 flight cycles after the effective date
of this AD.
Repair: Modified and Unmodified Skin Areas
(d) If any cracking is detected during any inspection required
by this AD: Do the actions specified by paragraph (d)(1) or (d)(2)
of this AD before further flight. Do the actions in accordance with
Boeing Service Bulletin 737-53-1065, Revision 2, dated April 19,
2001, except as required by paragraph (e) of this AD.
(1) Do a time-limited repair (including a detailed inspection of
the skin in the area of the repair to detect corrosion and doubler
disbonding) in accordance with Part III of the Accomplishment
Instructions of the service bulletin.
(i) After the time-limited repair has been accomplished: At
intervals not to exceed 3,000 flight cycles, perform an external
general visual inspection of the repair to detect loose or missing
fasteners, in accordance with Part III of the Accomplishment
Instructions of the service bulletin, until the actions specified in
paragraph (d)(1)(v) of this AD have been accomplished.
(ii) Within 4,500 flight cycles after the time-limited repair
has been accomplished: Perform an internal inspection of the repair
to detect cracking or doubler disbonding using general visual and
high-frequency eddy current methods, in accordance with Figure 11 of
the service bulletin, unless the actions specified in paragraph
(d)(1)(v) of this AD have been accomplished.
(iii) If any cracking is found during any inspection required by
paragraph (d)(1) of this AD: Repair before further flight in
accordance with paragraph (e) of this AD. Another approved repair
method is in Section 53-30-3, Figure 48, of the Boeing 737
Structural Repair Manual (SRM).
(iv) If any disbonding is found during any inspection required
by paragraph (d)(1) of this AD: Repair before further flight in
accordance with Part II of the service bulletin.
(v) Within 10,000 flight cycles after accomplishment of the
time-limited repair: Make the repair permanent in accordance with
Part III of the Accomplishment Instructions of the service bulletin.
Permanent repair of an area terminates the repetitive inspections
specified in this AD for that repaired area only.
(2) Do a permanent repair (including an inspection using
external subsurface eddy
[[Page 36831]]
current or magneto optical imaging methods to detect cracks at the
chem-milled step in each adjacent bay of the fuselage skin, a
detailed inspection of the skin in the area of the repair for
corrosion and doubler disbonding, and applicable corrective action)
of the cracked area, in accordance with Part II of the
Accomplishment Instructions of the service bulletin. Another
approved repair method is in Section 53-30-3, Figure 48, of the
Boeing 737 SRM. Permanent repair of an area terminates the
repetitive inspections specified in this AD for that repaired area
only.
Exceptions to Service Bulletin Procedures
(e) During any inspection required by this AD, if any
discrepancy (including cracking) is detected for which the service
bulletin specifies to contact Boeing for appropriation action:
Before further flight, repair according to a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA; or
according to data meeting the certification basis of the airplane
approved by an Authorized Representative for the Boeing 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.
(f) Although Boeing Service Bulletin 737-53-1065, Revision 2,
dated April 19, 2001, recommends that cracks found in Zone 2 be
reported to Boeing, this AD does not require such a report.
(g) For airplanes subject to the requirements of paragraphs (a)
and (c) of this AD: Inspections are not required in areas that are
spanned by an FAA-approved repair that has a minimum of 3 rows of
fasteners above and below the chemical-milled step. If an external
doubler covers the chemical-milled step, but does not span it by a
minimum of 3 rows of fasteners above and below, one method of
compliance with the inspection requirement of paragraphs (a) and (c)
of this AD is to inspect all chemical-milled steps covered by the
repair using internal nondestructive test (NDT) methods in
accordance with Part 6, Subject 53-30-20, of the Boeing 737 NDT
Manual. Follow-on and corrective actions must be done as specified
in this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
ACO, FAA, is authorized to approve AMOCs for this AD.
(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 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.
Incorporation by Reference
(i) Unless otherwise specified in this AD, the actions must be
done in accordance with Boeing Service Bulletin 737-53-1065,
Revision 2, dated April 19, 2001. This incorporation by reference
was approved by the Director of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this
service information, contact Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124-2207. To inspect copies of this
service information, go to the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or to 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.
Effective Date
(j) This amendment becomes effective on August 1, 2005.
Issued in Renton, Washington, on June 14, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-12503 Filed 6-24-05; 8:45 am]
BILLING CODE 4910-13-P
