Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR Series Airplanes, 59252-59256 [05-20072]
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Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations
acceptable for compliance with the
corresponding actions required by this AD.
Alternative Methods of Compliance (AMOCs)
(s)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19.
(2) 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.
(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.
(4) Alternative methods of compliance and
FAA-approved repairs, approved previously
in accordance with AD 2002–10–10 are
approved as AMOCs for the corresponding
actions required by this AD.
Material Incorporated by Reference
(t) You must use the service bulletins
specified in Table 1 of this AD, as applicable,
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approves the incorporation by reference of
Boeing Service Bulletin 747–53A2349,
Revision 2, dated April 3, 2003; and Boeing
Alert Service Bulletin 747–53A2452, dated
April 3, 2003; in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Alert Service Bulletin
747–53A2349, Revision 1, dated October 12,
2000, as of June 27, 2002 (67 FR 36081, May
23, 2002).
(3) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Service Bulletin 747–53–
2349, dated June 27, 1991, as of June 11, 1993
(58 FR 27927, May 12, 1993).
(4) 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.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Service bulletin
Boeing
Boeing
Boeing
Boeing
Alert Service Bulletin 747–53A2349 ................................................................................................
Alert Service Bulletin 747–53A2452 ................................................................................................
Service Bulletin 747–53–2349 .........................................................................................................
Service Bulletin 747–53A2349 ........................................................................................................
Issued in Renton, Washington, on
September 28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–20071 Filed 10–11–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20880; Directorate
Identifier 2003–NM–229–AD; Amendment
39–14327; AD 2005–20–30]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–300, 747SP, and
747SR Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747 series airplanes. That AD currently
requires repetitive inspections to detect
cracks in various areas of the fuselage
internal structure, and repair if
necessary. This new AD requires
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repetitive inspections of additional
areas of the fuselage internal structure,
and related investigative/corrective
actions if necessary. This new AD also
removes certain requirements from the
existing AD. This AD results from
fatigue testing of the fuselage structure
of a Boeing Model 747SR series
airplane. We are issuing this AD to
prevent the loss of the structural
integrity of the fuselage, which could
result in rapid depressurization of the
airplane.
Effective November 16, 2005.
The Director of the Federal Register
approved the incorporation by reference
of Boeing Service Bulletin 747–
53A2349, Revision 2, dated April 3,
2003, as of November 16, 2005.
On June 27, 2002 (67 FR 36081, May
23, 2002), the Director of the Federal
Register approved the incorporation by
reference of Boeing Alert Service
Bulletin 747–53A2349, Revision 1,
dated October 12, 2000.
On June 11, 1993 (58 FR 27927, May
12, 1993), the Director of the Federal
Register approved the incorporation by
reference of Boeing Service Bulletin
747–53–2349, dated June 27, 1991.
DATES:
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
ADDRESSES:
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1 ...............
Original ....
Original ....
2 ..............
Date
October 12, 2000
April 3, 2003.
June 27, 1991.
April 3, 2003.
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: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may 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 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
supersedes AD 2002–10–10, amendment
39–12756 (67 FR 36081, May 23, 2002).
The existing AD applies to certain
Boeing Model 747 series airplanes. That
NPRM was published in the Federal
Register on April 11, 2005 (70 FR
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18332). That NPRM proposed to require
repetitive inspections to detect cracks in
various areas of the fuselage internal
structure, and related investigative/
corrective actions if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Request To Clarify Paragraph (b) of the
NPRM
One commenter, the manufacturer,
requests that paragraph (b) of the NPRM
be revised to indicate that the NPRM
does not address the upper deck floor
beams, one subject of AD 2002–10–10.
The commenter suggests that paragraph
(b) be revised to read, ‘‘This AD
supersedes AD 2002–10–10, amendment
39–12756 (67 FR 36081, May 23, 2002),
except AD 2002–10–10, paragraphs
(a)(1), (d), (e), and (g), are not addressed
by this AD.’’
We do not agree. In the ‘‘Other
Related Rulemaking’’ section of the
NPRM, we clarified that all
requirements from AD 2002–10–10
related to the upper deck floor beams
are included in a separate rulemaking
action. Consequently, on April 1, 2005,
we issued an NPRM, Docket No. FAA–
2005–20879, to propose to address
cracking in the upper chords of the
upper deck floor beams. That NPRM
was published in the Federal Register
on April 11, 2005 (70 FR 18327). We
have not revised the final rule in this
regard.
Request To Revise Paragraph (i) of the
NPRM
The same commenter requests that
paragraph (i) of the NPRM be revised to
indicate that the inspection for the areas
specified in paragraph (i)(5) of the
NPRM consists of internal and external
detailed inspections. The commenter
notes that the revision should be made
to agree with Boeing Service Bulletin
747–53A2349, Revision 2, dated April 3,
2003 (which is referenced as the
appropriate source of service
information for accomplishing the
proposed actions).
We agree with the commenter. The
inspections of the nose wheel well
bulkheads and floor beams specified in
paragraph (i)(5) of the final rule are
internal and external inspections. We
have revised paragraph (i) of the final
rule accordingly.
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Request To Move Grace Period From
Paragraph (j)(2) to Paragraph (j)(1)
The same commenter requests that the
grace period ‘‘within 1,000 flight cycles
after the effective date of this AD,’’ be
removed from the compliance time in
paragraph (j)(2) of the NPRM and be
added to the compliance time in
paragraph (j)(1) of the NPRM. The
commenter believes moving the grace
period will convey the true intent of the
service bulletin. The commenter states
that the grace period can be removed
from paragraph (j)(2) because the
paragraph applies to operators that have
already performed the inspections
specified in paragraphs (i)(5) and (i)(7)
of the NPRM. The commenter explains
that these operators therefore are using
Revision 2 of the service bulletin and
would continue the inspections at the
3,000-flight-cycle repetitive interval.
We partially agree with the
commenter. We agree with the
commenter that the grace period
‘‘within 1,000 flight cycles after the
effective date of this AD’’ should be
added to the compliance time in
paragraph (j)(1) of the final rule and
have revised paragraph (j)(1)
accordingly. We find that the grace
period will keep airplanes from being
grounded unnecessarily and will
provide an acceptable level of safety.
However, we do not agree to remove the
grace period from paragraph (j)(2) of the
final rule. Operators that have
voluntarily accomplished the
inspections specified in paragraphs
(i)(5) and (i)(7) of the final rule before
the effective date of the final rule should
be given the same grace period for the
new inspections as operators that have
not done the inspections specified in
paragraphs (i)(5) and (i)(7). We also note
that this grace period is for the new
inspections specified in paragraphs
(i)(5) and (i)(7) and that operators are
still required to do the inspections
specified in paragraph (f) of the final
rule at intervals not to exceed 3,000
flight cycles until all the inspections
required by paragraph (i) of the final
rule are done.
Request To Revise Compliance Time in
Paragraph (j)(3)
The same commenter requests that the
compliance time specified in paragraph
(j)(3) of the NPRM be revised to clarify
that the grace period is limited to the
‘‘new work’’ specified in paragraphs
(i)(5) and (i)(7) of the NPRM. The
commenter states that the existing
compliance time would allow deferral
of all the inspections until 23,000 total
flight cycles. The commenter
recommends that the compliance time
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59253
read as follows: ‘‘Accomplish the
inspections required by paragraphs
(i)(1), (i)(2), (i)(3), (i)(4), (f)(5), and (i)(6)
of this AD prior to the accumulation of
22,000 flight cycles. Accomplish the
inspections required by paragraphs (i)(5)
and (i)(7) of this AD prior to the
accumulation of 22,000 flight cycles, or
within 1,000 flight cycles after the
effective date of this AD, whichever is
later.’’
We acknowledge that the only new
inspections required by the final rule
are the inspections specified in
paragraphs (i)(5) and (i)(7) of the final
rule. However, we do not agree that the
compliance time specified in paragraph
(j)(3) of the final rule allows for deferral
of the other inspections specified in
paragraph (i) of the final rule. Although
an operator may delay doing the
inspections specified in paragraphs
(i)(1), (i)(2), (i)(3), (i)(4), and (i)(6) of the
final rule until the end of the grace
period, the operator is still required to
do the equivalent inspections specified
in paragraph (f) of the final rule. Thus
the existing inspections required by
paragraph (f) of the final rule must be
done at the compliance times specified
in paragraph (f) until all the inspections
required by paragraph (i) are done. We
have not changed the final rule in this
regard.
Request To Clarify Repair Reference
The same commenter requests that
paragraphs (h) and (k) of the NPRM be
revised to clarify that the Boeing
Structural Repair Manuals (SRMs) meet
the intent of the NPRM for repairs. The
commenter contends that the SRMs
contain the appropriate repairs and are
referenced in Boeing Service Bulletin
747–53–2349. The commenter believes
that the phrase ‘‘For a repair method to
be approved, the approval must
specifically reference this AD’’ in the
second part of paragraph (k) should
apply only to the second part of the
paragraph that says to ‘‘contact Boeing.’’
The commenter notes that some
operators may have already done the
repair per the SRM and suggests it
would be best to state that the SRMs
meet the intent of the AD.
We partially agree with the
commenter. We agree with the
commenter that the SRM procedures
referenced in the service bulletin are an
appropriate source of service
information for doing the repairs
required by the final rule. We have
revised paragraph (h) of the final rule to
allow operators to do repairs in
accordance with Boeing Service Bulletin
747–53A2349, Revision 2, as specified
in paragraph (k) of the final rule.
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However, we do not agree to revise
paragraph (k) of the final rule to state
that the SRM meets the intent of the
final rule because paragraph (k)
specifies to do the repair in accordance
with Boeing Service Bulletin 747–
53A2349, Revision 2, which references
the SRM. Therefore, operators that do
the repair in accordance with the
applicable SRM referenced in the
service bulletin meet the repair
requirement of the final rule and do not
need further FAA approval. Paragraph
(k) of the final rule specifies to repair in
accordance with FAA approval only
where the service bulletin specifies to
contact Boeing for repair. Thus,
operators are required to obtain FAA
approval only for repairs that are
beyond the scope of the service bulletin
or SRM. As the commenter noted, the
phrase, ‘‘For a repair method to be
approved, the approval must
specifically reference this AD,’’ applies
only to operators that are required to
obtain FAA approval. We have not
revised the final rule in this regard.
Request To Include Effect of AD 2004–
07–22 on the NPRM
Two commenters request that the
NPRM include the effect of AD 2004–
07–22, amendment 39–13566 (69 FR
18250, April 7, 2004), which mandates
Boeing Document No. D6–35022,
‘‘Supplemental Structural Inspection
Document,’’ (SSID) for Model 747
Airplanes, Revision G, dated December
2000. One commenter states that it has
done the SSID inspections required by
AD 2004–07–22 and that the NPRM may
include inspections already covered by
the SSID inspections. The commenter
suggests that, to prevent duplicate work,
the NPRM should identify the
paragraphs for which SSID inspections
are acceptable as an alternative method
of compliance (AMOC). The other
commenter, the manufacturer, notes that
the SSID includes statements that allow
the use of Boeing Service Bulletin 747–
53–2349 inspections in lieu of SSID
inspections. The commenter notes that,
because of the NPRM, there will be a
requirement to perform the SSID
inspections and the Boeing Service
Bulletin 747–53–2349 inspections
without an allowance to use the service
bulletin inspections as a substitute for
the SSID inspections. The commenter
contends that it is better to have an
operator use the service bulletin
inspections due to the improved level of
detailed instructions.
We acknowledge that certain
inspections done in accordance with
Boeing Service Bulletin 747–53–2349
may be acceptable as a substitute for
corresponding SSID inspections and
vice versa, because inspections done in
accordance with both documents cover
common areas. However, operators must
identify the inspections and substantiate
that any substitutions would provide an
acceptable level of safety, and we must
approve any substitutions. In order to
avoid further delay to the inspections
required by this final rule, we have not
revised the final rule in this regard.
Operators may request approval for
AMOCs according to paragraph (m) of
this final rule. For AD 2004–07–22,
operators may request approval for
AMOCs according to paragraph (g) of
that AD.
Explanation of Change Made to This
Final Rule
We have simplified paragraphs (h)(1),
(h)(2), and (k) of this AD by referring to
the ‘‘Alternative Methods of Compliance
(AMOCs)’’ paragraph (m) of this final
rule for repair methods.
Clarification of AMOC Paragraph
We have revised this final rule 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 received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
This AD will affect about 489
airplanes worldwide, and 155 airplanes
of U.S. registry. The following table
provides the estimated costs for U.S.
operators to comply with this AD.
ESTIMATED COSTS
Work
hours
Action
Inspections, excluding upper deck floor beams, per inspection cycle (required by AD 2002–10–10).
Inspections (new AD) ........................................................................................
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
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Average
labor
rate per
hour
Parts
Cost per
airplane,
per inspection cycle
Number
of U.S.registered
airplanes
145
$65
None
$9,425
155
$1,460,875
130
65
None
8,450
155
1,309,750
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,
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Fleet cost
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
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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
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 removing amendment 39–12756 (67
FR 36081, May 23, 2002) and by adding
the following new airworthiness
directive (AD):
I
2005–20–30 Boeing: Amendment 39–14327.
Docket No. FAA–2005–20880;
Directorate Identifier 2003–NM–229–AD.
Effective Date
(a) This AD becomes effective November
16, 2005.
Affected ADs
(b) This AD supersedes AD 2002–10–10.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–300, 747SP, and 747SR series airplanes;
certificated in any category; identified in
Boeing Service Bulletin 747–53A2349,
Revision 2, dated April 3, 2003.
Unsafe Condition
(d) This AD was prompted by the results
of fatigue testing of the fuselage structure of
a Boeing Model 747SR series airplane. We
are issuing this AD to prevent the loss of the
structural integrity of the fuselage, which
could result in rapid depressurization 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.
Restatement of Requirements of AD 2002–
10–10 (Excluding Upper Deck Floor Beams)
Repetitive Inspections
(f) Prior to the accumulation of 22,000 total
flight cycles, or within 1,000 flight cycles
after June 11, 1993 (the effective date of AD
93–08–12, amendment 39–8559), whichever
occurs later, unless accomplished previously
within the last 2,000 flight cycles; and
thereafter at intervals not to exceed 3,000
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flight cycles: Perform an internal detailed
inspection to detect cracks in the areas of the
fuselage internal structure specified in
paragraphs (f)(1) through (f)(6) of this AD; in
accordance with Boeing Service Bulletin
747–53–2349, dated June 27, 1991; Boeing
Alert Service Bulletin 747–53A2349,
Revision 1, dated October 12, 2000; or Boeing
Service Bulletin 747–53A2349, Revision 2,
dated April 3, 2003. After the effective date
of this AD, only Revision 2 of Boeing Service
Bulletin 747–53A2349 may be used.
Continue doing the inspections until the
inspections required by paragraph (i) of this
AD are done.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Section 41 body station 260, 340, and
400 bulkheads.
(6) Main entry doors.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(g) Prior to the accumulation of 25,000 total
flight cycles, or within 1,000 flight cycles
after June 11, 1993, whichever is later, unless
already done within the last 2,000 flight
cycles; and thereafter at intervals not to
exceed 3,000 flight cycles: Do an internal
detailed inspection to detect cracks in the
Section 46 upper lobe frames, in accordance
with Boeing Service Bulletin 747–53–2349,
dated June 27, 1991; Boeing Alert Service
Bulletin 747–53A2349, Revision 1, dated
October 12, 2000; or Boeing Service Bulletin
747–53A2349, Revision 2, dated April 3,
2003. After the effective date of this AD, only
Revision 2 of Boeing Service Bulletin 747–
53A2349 may be used.
Repair of Cracks Detected During Paragraph
(f) or (g) Inspections
(h) Before further flight, repair any cracks
detected during the inspections done per
paragraph (f) or (g) of this AD by doing the
actions specified in paragraph (h)(1) or (h)(2)
of this AD, as applicable.
(1) Repair in accordance with a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or using a
method approved in accordance with
paragraph (m) of this AD.
(2) Repair in accordance with Boeing
Service Bulletin 747–53A2349, Revision 2,
dated April 3, 2003. Where the service
bulletin specifies to contact Boeing for repair
instructions, repair in accordance with a
method approved by the Manager, Seattle
ACO; or using a method approved in
accordance with paragraph (m) of this AD.
New Requirements of This AD
Repetitive Inspections
(i) Do an internal detailed inspection to
detect cracking in the areas of the fuselage
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59255
internal structure specified in paragraphs
(i)(1), (i)(2), and (i)(3) of this AD, and internal
and external detailed inspections of the areas
specified in paragraphs (i)(4), (i)(5), (i)(6),
and (i)(7) of this AD. Do the inspections in
accordance with Boeing Service Bulletin
747–53A2349, Revision 2, dated April 3,
2003. Do the inspections at the applicable
time specified in paragraph (j) of this AD.
Accomplishment of these inspections
terminates the requirements of paragraph (f)
of this AD.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Nose wheel well bulkheads, sidewall
panels, and the STA 360 and 380 floor
beams. These areas include the Section 41
body station 260, 340, and 400 bulkheads.
(6) Main entry doors.
(7) Main electronics bay access door
cutout.
(j) Do the inspections required by
paragraph (i) of this AD at the applicable
time specified in paragraph (j)(1), (j)(2), or
(j)(3) of this AD. Repeat the inspections
thereafter at intervals not to exceed 3,000
flight cycles.
(1) For airplanes on which the inspections
required by paragraphs (f)(1), (f)(2), (f)(3),
(f)(4), and (f)(6) of this AD have been done
before the effective date of this AD, but the
inspections required by paragraphs (i)(5) and
(i)(7) of this AD have not been done: Within
3,000 flight cycles since accomplishment of
the most recent inspection required by
paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(6)
of this AD, except the inspections specified
in paragraphs (i)(5) and (i)(7) of this AD may
be done within 3,000 flight cycles since
accomplishment of the most recent
inspection required by paragraphs (f)(1),
(f)(2), (f)(3), (f)(4), and (f)(6) of this AD, or
within 1,000 flight cycles after the effective
date of this AD, whichever is later.
(2) For airplanes on which the inspections
required by paragraphs (i)(5) and (i)(7) have
been done before the effective date of this
AD: Within 3,000 flight cycles since
accomplishment of the most recent
inspection required by paragraphs (i)(5) and
(i)(7) of this AD, or within 1,000 flight cycles
after the effective date of this AD, whichever
is later.
(3) For airplanes on which the inspections
required by paragraph (f) of this AD have not
been done before the effective date of this
AD: Prior to the accumulation of 22,000 total
flight cycles, or within 1,000 flight cycles
after the effective date of this AD, whichever
is later.
Repair of Cracks Detected During Paragraph
(i) Inspection
(k) Before further flight, repair any cracking
found during any inspection required by
paragraph (i) of this AD in accordance with
Boeing Service Bulletin 747–53A2349,
Revision 2, dated April 3, 2003. Where the
service bulletin specifies to contact Boeing
for repair instructions, repair in accordance
with a method approved by the Manager,
Seattle ACO; or using a method approved in
accordance with paragraph (m) of this AD.
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12OCR1
59256
Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations
Actions Previously Accomplished
(l) Inspections required by paragraph (i) of
this AD, accomplished before the effective
date of this AD, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–53–2349, dated June 27,
1991; or Boeing Alert Service Bulletin 747–
53A2349, Revision 1, dated October 12, 2000;
are acceptable for compliance with the
corresponding action required by paragraph
(i) of this AD.
Alternative Methods of Compliance
(AMOCs)
(m)(1) The Manager, Seattle ACO, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19.
(2) 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.
(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.
(4) Alternative methods of compliance and
FAA-approved repairs, approved previously
in accordance with AD 2002–10–10 or AD
93–08–12, are approved as alternative
methods of compliance with the
corresponding requirements of this AD.
Material Incorporated by Reference
(n) You must use Boeing Service Bulletin
747–53–2349, dated June 27, 1991; Boeing
Alert Service Bulletin 747–53A2349,
Revision 1, dated October 12, 2000; or Boeing
Service Bulletin 747–53A2349, Revision 2,
dated April 3, 2003; to perform the actions
that are required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approves the incorporation by reference of
Boeing Service Bulletin 747–53A2349,
Revision 2, dated April 3, 2003, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Alert Service Bulletin
747–53A2349, Revision 1, dated October 12,
2000, as of June 27, 2002 (67 FR 36081, May
23, 2002).
(3) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Service Bulletin 747–53–
2349, dated June 27, 1991, as of June 11, 1993
(58 FR 27927, May 12, 1993).
(4) To get copies of the service information,
contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207.
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
VerDate Aug<31>2005
16:47 Oct 11, 2005
Jkt 208001
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. 05–20072 Filed 10–11–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20687; Directorate
Identifier 2004–NM–171–AD; Amendment
39–14325; AD 2005–20–28]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319–100 Series Airplanes; Model
A320–111 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
floor proximity emergency escape path
marking system. This AD results from
information that the existing system
design for interconnection of the
emergency power supply units of the
floor proximity emergency escape path
marking system does not provide
adequate floor path lighting and
marking for safe evacuation of the
airplane in the event of an emergency.
We are issuing this AD to prevent
inadequate lighting and marking of the
escape path, which could delay or
impede the flightcrew and passengers
when exiting the airplane during an
emergency landing.
DATES: This AD becomes effective
November 16, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 16, 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
PO 00000
Frm 00048
Fmt 4700
Sfmt 4700
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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
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 March 23, 2005 (70 FR
14597). That NPRM proposed to require
modifying the floor proximity
emergency escape path marking system
(FPEEPMS).
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Clarify Certain Sections in
the Preamble
One commenter disagrees with the
implication that Bruce Industries
equipment is the root cause of the
unsafe condition. The commenter states
that the language in the Discussion
section of the NPRM indicates that the
root cause of the unsafe condition is the
design of the Bruce power supply. The
commenter adds that this is not the
case, and notes that the problem is not
with the design but with the method of
installing that component on the
airplane. The commenter states that it
contacted Airbus regarding this
problem, and Airbus responded by
identifying the source of the problem as
the incorrect installation of the Bruce
power supply and the wiring on the
airplane. Airbus and Bruce Industries
have since developed a resolution. The
E:\FR\FM\12OCR1.SGM
12OCR1
]]>Agencies
[Federal Register Volume 70, Number 196 (Wednesday, October 12, 2005)]
[Rules and Regulations]
[Pages 59252-59256]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-20072]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20880; Directorate Identifier 2003-NM-229-AD;
Amendment 39-14327; AD 2005-20-30]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-300, 747SP, and 747SR Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747 series airplanes. That
AD currently requires repetitive inspections to detect cracks in
various areas of the fuselage internal structure, and repair if
necessary. This new AD requires repetitive inspections of additional
areas of the fuselage internal structure, and related investigative/
corrective actions if necessary. This new AD also removes certain
requirements from the existing AD. This AD results from fatigue testing
of the fuselage structure of a Boeing Model 747SR series airplane. We
are issuing this AD to prevent the loss of the structural integrity of
the fuselage, which could result in rapid depressurization of the
airplane.
DATES: Effective November 16, 2005.
The Director of the Federal Register approved the incorporation by
reference of Boeing Service Bulletin 747-53A2349, Revision 2, dated
April 3, 2003, as of November 16, 2005.
On June 27, 2002 (67 FR 36081, May 23, 2002), the Director of the
Federal Register approved the incorporation by reference of Boeing
Alert Service Bulletin 747-53A2349, Revision 1, dated October 12, 2000.
On June 11, 1993 (58 FR 27927, May 12, 1993), the Director of the
Federal Register approved the incorporation by reference of Boeing
Service Bulletin 747-53-2349, dated June 27, 1991.
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: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may 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 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 supersedes AD 2002-10-10, amendment
39-12756 (67 FR 36081, May 23, 2002). The existing AD applies to
certain Boeing Model 747 series airplanes. That NPRM was published in
the Federal Register on April 11, 2005 (70 FR
[[Page 59253]]
18332). That NPRM proposed to require repetitive inspections to detect
cracks in various areas of the fuselage internal structure, and related
investigative/corrective actions if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Clarify Paragraph (b) of the NPRM
One commenter, the manufacturer, requests that paragraph (b) of the
NPRM be revised to indicate that the NPRM does not address the upper
deck floor beams, one subject of AD 2002-10-10. The commenter suggests
that paragraph (b) be revised to read, ``This AD supersedes AD 2002-10-
10, amendment 39-12756 (67 FR 36081, May 23, 2002), except AD 2002-10-
10, paragraphs (a)(1), (d), (e), and (g), are not addressed by this
AD.''
We do not agree. In the ``Other Related Rulemaking'' section of the
NPRM, we clarified that all requirements from AD 2002-10-10 related to
the upper deck floor beams are included in a separate rulemaking
action. Consequently, on April 1, 2005, we issued an NPRM, Docket No.
FAA-2005-20879, to propose to address cracking in the upper chords of
the upper deck floor beams. That NPRM was published in the Federal
Register on April 11, 2005 (70 FR 18327). We have not revised the final
rule in this regard.
Request To Revise Paragraph (i) of the NPRM
The same commenter requests that paragraph (i) of the NPRM be
revised to indicate that the inspection for the areas specified in
paragraph (i)(5) of the NPRM consists of internal and external detailed
inspections. The commenter notes that the revision should be made to
agree with Boeing Service Bulletin 747-53A2349, Revision 2, dated April
3, 2003 (which is referenced as the appropriate source of service
information for accomplishing the proposed actions).
We agree with the commenter. The inspections of the nose wheel well
bulkheads and floor beams specified in paragraph (i)(5) of the final
rule are internal and external inspections. We have revised paragraph
(i) of the final rule accordingly.
Request To Move Grace Period From Paragraph (j)(2) to Paragraph (j)(1)
The same commenter requests that the grace period ``within 1,000
flight cycles after the effective date of this AD,'' be removed from
the compliance time in paragraph (j)(2) of the NPRM and be added to the
compliance time in paragraph (j)(1) of the NPRM. The commenter believes
moving the grace period will convey the true intent of the service
bulletin. The commenter states that the grace period can be removed
from paragraph (j)(2) because the paragraph applies to operators that
have already performed the inspections specified in paragraphs (i)(5)
and (i)(7) of the NPRM. The commenter explains that these operators
therefore are using Revision 2 of the service bulletin and would
continue the inspections at the 3,000-flight-cycle repetitive interval.
We partially agree with the commenter. We agree with the commenter
that the grace period ``within 1,000 flight cycles after the effective
date of this AD'' should be added to the compliance time in paragraph
(j)(1) of the final rule and have revised paragraph (j)(1) accordingly.
We find that the grace period will keep airplanes from being grounded
unnecessarily and will provide an acceptable level of safety. However,
we do not agree to remove the grace period from paragraph (j)(2) of the
final rule. Operators that have voluntarily accomplished the
inspections specified in paragraphs (i)(5) and (i)(7) of the final rule
before the effective date of the final rule should be given the same
grace period for the new inspections as operators that have not done
the inspections specified in paragraphs (i)(5) and (i)(7). We also note
that this grace period is for the new inspections specified in
paragraphs (i)(5) and (i)(7) and that operators are still required to
do the inspections specified in paragraph (f) of the final rule at
intervals not to exceed 3,000 flight cycles until all the inspections
required by paragraph (i) of the final rule are done.
Request To Revise Compliance Time in Paragraph (j)(3)
The same commenter requests that the compliance time specified in
paragraph (j)(3) of the NPRM be revised to clarify that the grace
period is limited to the ``new work'' specified in paragraphs (i)(5)
and (i)(7) of the NPRM. The commenter states that the existing
compliance time would allow deferral of all the inspections until
23,000 total flight cycles. The commenter recommends that the
compliance time read as follows: ``Accomplish the inspections required
by paragraphs (i)(1), (i)(2), (i)(3), (i)(4), (f)(5), and (i)(6) of
this AD prior to the accumulation of 22,000 flight cycles. Accomplish
the inspections required by paragraphs (i)(5) and (i)(7) of this AD
prior to the accumulation of 22,000 flight cycles, or within 1,000
flight cycles after the effective date of this AD, whichever is
later.''
We acknowledge that the only new inspections required by the final
rule are the inspections specified in paragraphs (i)(5) and (i)(7) of
the final rule. However, we do not agree that the compliance time
specified in paragraph (j)(3) of the final rule allows for deferral of
the other inspections specified in paragraph (i) of the final rule.
Although an operator may delay doing the inspections specified in
paragraphs (i)(1), (i)(2), (i)(3), (i)(4), and (i)(6) of the final rule
until the end of the grace period, the operator is still required to do
the equivalent inspections specified in paragraph (f) of the final
rule. Thus the existing inspections required by paragraph (f) of the
final rule must be done at the compliance times specified in paragraph
(f) until all the inspections required by paragraph (i) are done. We
have not changed the final rule in this regard.
Request To Clarify Repair Reference
The same commenter requests that paragraphs (h) and (k) of the NPRM
be revised to clarify that the Boeing Structural Repair Manuals (SRMs)
meet the intent of the NPRM for repairs. The commenter contends that
the SRMs contain the appropriate repairs and are referenced in Boeing
Service Bulletin 747-53-2349. The commenter believes that the phrase
``For a repair method to be approved, the approval must specifically
reference this AD'' in the second part of paragraph (k) should apply
only to the second part of the paragraph that says to ``contact
Boeing.'' The commenter notes that some operators may have already done
the repair per the SRM and suggests it would be best to state that the
SRMs meet the intent of the AD.
We partially agree with the commenter. We agree with the commenter
that the SRM procedures referenced in the service bulletin are an
appropriate source of service information for doing the repairs
required by the final rule. We have revised paragraph (h) of the final
rule to allow operators to do repairs in accordance with Boeing Service
Bulletin 747-53A2349, Revision 2, as specified in paragraph (k) of the
final rule.
[[Page 59254]]
However, we do not agree to revise paragraph (k) of the final rule
to state that the SRM meets the intent of the final rule because
paragraph (k) specifies to do the repair in accordance with Boeing
Service Bulletin 747-53A2349, Revision 2, which references the SRM.
Therefore, operators that do the repair in accordance with the
applicable SRM referenced in the service bulletin meet the repair
requirement of the final rule and do not need further FAA approval.
Paragraph (k) of the final rule specifies to repair in accordance with
FAA approval only where the service bulletin specifies to contact
Boeing for repair. Thus, operators are required to obtain FAA approval
only for repairs that are beyond the scope of the service bulletin or
SRM. As the commenter noted, the phrase, ``For a repair method to be
approved, the approval must specifically reference this AD,'' applies
only to operators that are required to obtain FAA approval. We have not
revised the final rule in this regard.
Request To Include Effect of AD 2004-07-22 on the NPRM
Two commenters request that the NPRM include the effect of AD 2004-
07-22, amendment 39-13566 (69 FR 18250, April 7, 2004), which mandates
Boeing Document No. D6-35022, ``Supplemental Structural Inspection
Document,'' (SSID) for Model 747 Airplanes, Revision G, dated December
2000. One commenter states that it has done the SSID inspections
required by AD 2004-07-22 and that the NPRM may include inspections
already covered by the SSID inspections. The commenter suggests that,
to prevent duplicate work, the NPRM should identify the paragraphs for
which SSID inspections are acceptable as an alternative method of
compliance (AMOC). The other commenter, the manufacturer, notes that
the SSID includes statements that allow the use of Boeing Service
Bulletin 747-53-2349 inspections in lieu of SSID inspections. The
commenter notes that, because of the NPRM, there will be a requirement
to perform the SSID inspections and the Boeing Service Bulletin 747-53-
2349 inspections without an allowance to use the service bulletin
inspections as a substitute for the SSID inspections. The commenter
contends that it is better to have an operator use the service bulletin
inspections due to the improved level of detailed instructions.
We acknowledge that certain inspections done in accordance with
Boeing Service Bulletin 747-53-2349 may be acceptable as a substitute
for corresponding SSID inspections and vice versa, because inspections
done in accordance with both documents cover common areas. However,
operators must identify the inspections and substantiate that any
substitutions would provide an acceptable level of safety, and we must
approve any substitutions. In order to avoid further delay to the
inspections required by this final rule, we have not revised the final
rule in this regard. Operators may request approval for AMOCs according
to paragraph (m) of this final rule. For AD 2004-07-22, operators may
request approval for AMOCs according to paragraph (g) of that AD.
Explanation of Change Made to This Final Rule
We have simplified paragraphs (h)(1), (h)(2), and (k) of this AD by
referring to the ``Alternative Methods of Compliance (AMOCs)''
paragraph (m) of this final rule for repair methods.
Clarification of AMOC Paragraph
We have revised this final rule 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 received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD will affect about 489 airplanes worldwide, and 155
airplanes of U.S. registry. The following table provides the estimated
costs for U.S. operators to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Average airplane, Number of
Action Work labor Parts per U.S.- Fleet cost
hours rate per inspection registered
hour cycle airplanes
----------------------------------------------------------------------------------------------------------------
Inspections, excluding upper deck floor 145 $65 None............ $9,425 155 $1,460,875
beams, per inspection cycle (required
by AD 2002-10-10).
Inspections (new AD)................... 130 65 None............ 8,450 155 1,309,750
----------------------------------------------------------------------------------------------------------------
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
[[Page 59255]]
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
removing amendment 39-12756 (67 FR 36081, May 23, 2002) and by adding
the following new airworthiness directive (AD):
2005-20-30 Boeing: Amendment 39-14327. Docket No. FAA-2005-20880;
Directorate Identifier 2003-NM-229-AD.
Effective Date
(a) This AD becomes effective November 16, 2005.
Affected ADs
(b) This AD supersedes AD 2002-10-10.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes;
certificated in any category; identified in Boeing Service Bulletin
747-53A2349, Revision 2, dated April 3, 2003.
Unsafe Condition
(d) This AD was prompted by the results of fatigue testing of
the fuselage structure of a Boeing Model 747SR series airplane. We
are issuing this AD to prevent the loss of the structural integrity
of the fuselage, which could result in rapid depressurization 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.
Restatement of Requirements of AD 2002-10-10 (Excluding Upper Deck
Floor Beams)
Repetitive Inspections
(f) Prior to the accumulation of 22,000 total flight cycles, or
within 1,000 flight cycles after June 11, 1993 (the effective date
of AD 93-08-12, amendment 39-8559), whichever occurs later, unless
accomplished previously within the last 2,000 flight cycles; and
thereafter at intervals not to exceed 3,000 flight cycles: Perform
an internal detailed inspection to detect cracks in the areas of the
fuselage internal structure specified in paragraphs (f)(1) through
(f)(6) of this AD; in accordance with Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; or Boeing Service
Bulletin 747-53A2349, Revision 2, dated April 3, 2003. After the
effective date of this AD, only Revision 2 of Boeing Service
Bulletin 747-53A2349 may be used. Continue doing the inspections
until the inspections required by paragraph (i) of this AD are done.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Section 41 body station 260, 340, and 400 bulkheads.
(6) Main entry doors.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(g) Prior to the accumulation of 25,000 total flight cycles, or
within 1,000 flight cycles after June 11, 1993, whichever is later,
unless already done within the last 2,000 flight cycles; and
thereafter at intervals not to exceed 3,000 flight cycles: Do an
internal detailed inspection to detect cracks in the Section 46
upper lobe frames, in accordance with Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; or Boeing Service
Bulletin 747-53A2349, Revision 2, dated April 3, 2003. After the
effective date of this AD, only Revision 2 of Boeing Service
Bulletin 747-53A2349 may be used.
Repair of Cracks Detected During Paragraph (f) or (g) Inspections
(h) Before further flight, repair any cracks detected during the
inspections done per paragraph (f) or (g) of this AD by doing the
actions specified in paragraph (h)(1) or (h)(2) of this AD, as
applicable.
(1) Repair in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or using a method
approved in accordance with paragraph (m) of this AD.
(2) Repair in accordance with Boeing Service Bulletin 747-
53A2349, Revision 2, dated April 3, 2003. Where the service bulletin
specifies to contact Boeing for repair instructions, repair in
accordance with a method approved by the Manager, Seattle ACO; or
using a method approved in accordance with paragraph (m) of this AD.
New Requirements of This AD
Repetitive Inspections
(i) Do an internal detailed inspection to detect cracking in the
areas of the fuselage internal structure specified in paragraphs
(i)(1), (i)(2), and (i)(3) of this AD, and internal and external
detailed inspections of the areas specified in paragraphs (i)(4),
(i)(5), (i)(6), and (i)(7) of this AD. Do the inspections in
accordance with Boeing Service Bulletin 747-53A2349, Revision 2,
dated April 3, 2003. Do the inspections at the applicable time
specified in paragraph (j) of this AD. Accomplishment of these
inspections terminates the requirements of paragraph (f) of this AD.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Nose wheel well bulkheads, sidewall panels, and the STA 360
and 380 floor beams. These areas include the Section 41 body station
260, 340, and 400 bulkheads.
(6) Main entry doors.
(7) Main electronics bay access door cutout.
(j) Do the inspections required by paragraph (i) of this AD at
the applicable time specified in paragraph (j)(1), (j)(2), or (j)(3)
of this AD. Repeat the inspections thereafter at intervals not to
exceed 3,000 flight cycles.
(1) For airplanes on which the inspections required by
paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(6) of this AD
have been done before the effective date of this AD, but the
inspections required by paragraphs (i)(5) and (i)(7) of this AD have
not been done: Within 3,000 flight cycles since accomplishment of
the most recent inspection required by paragraphs (f)(1), (f)(2),
(f)(3), (f)(4), and (f)(6) of this AD, except the inspections
specified in paragraphs (i)(5) and (i)(7) of this AD may be done
within 3,000 flight cycles since accomplishment of the most recent
inspection required by paragraphs (f)(1), (f)(2), (f)(3), (f)(4),
and (f)(6) of this AD, or within 1,000 flight cycles after the
effective date of this AD, whichever is later.
(2) For airplanes on which the inspections required by
paragraphs (i)(5) and (i)(7) have been done before the effective
date of this AD: Within 3,000 flight cycles since accomplishment of
the most recent inspection required by paragraphs (i)(5) and (i)(7)
of this AD, or within 1,000 flight cycles after the effective date
of this AD, whichever is later.
(3) For airplanes on which the inspections required by paragraph
(f) of this AD have not been done before the effective date of this
AD: Prior to the accumulation of 22,000 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever is later.
Repair of Cracks Detected During Paragraph (i) Inspection
(k) Before further flight, repair any cracking found during any
inspection required by paragraph (i) of this AD in accordance with
Boeing Service Bulletin 747-53A2349, Revision 2, dated April 3,
2003. Where the service bulletin specifies to contact Boeing for
repair instructions, repair in accordance with a method approved by
the Manager, Seattle ACO; or using a method approved in accordance
with paragraph (m) of this AD.
[[Page 59256]]
Actions Previously Accomplished
(l) Inspections required by paragraph (i) of this AD,
accomplished before the effective date of this AD, in accordance
with the Accomplishment Instructions of Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; or Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; are acceptable for
compliance with the corresponding action required by paragraph (i)
of this AD.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19.
(2) 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.
(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.
(4) Alternative methods of compliance and FAA-approved repairs,
approved previously in accordance with AD 2002-10-10 or AD 93-08-12,
are approved as alternative methods of compliance with the
corresponding requirements of this AD.
Material Incorporated by Reference
(n) You must use Boeing Service Bulletin 747-53-2349, dated June
27, 1991; Boeing Alert Service Bulletin 747-53A2349, Revision 1,
dated October 12, 2000; or Boeing Service Bulletin 747-53A2349,
Revision 2, dated April 3, 2003; to perform the actions that are
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approves the
incorporation by reference of Boeing Service Bulletin 747-53A2349,
Revision 2, dated April 3, 2003, in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000, as of June 27, 2002 (67
FR 36081, May 23, 2002).
(3) The Director of the Federal Register previously approved the
incorporation by reference of Boeing Service Bulletin 747-53-2349,
dated June 27, 1991, as of June 11, 1993 (58 FR 27927, May 12,
1993).
(4) To get copies of the service information, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
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. 05-20072 Filed 10-11-05; 8:45 am]
BILLING CODE 4910-13-P
