Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR Series Airplanes, 13349-13353 [05-5388]
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
Service Bulletin 747–71–2300, Revision 1,
dated October 30, 2003. Any applicable
corrective actions must be done before
further flight.
DEPARTMENT OF TRANSPORTATION
On Condition: Removal of Bulb Seals and
Other Specified Actions
14 CFR Part 39
(g) If bulb seals were installed on the
trailing edge of the fan thrust reverser in
accordance with Boeing Service Letter 747–
SL–71–045: Concurrently with or before
further flight after accomplishing paragraph
(f) of this AD, remove the bulb seals, plug the
open holes in the trailing edge of the fan
thrust reverser, and adjust the cowl latches
as applicable, in accordance with Boeing
Service Letter 747–SL–71–045–C, dated April
10, 2003.
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
Material Incorporated by Reference
(i) You must use Boeing Service Bulletin
747–71–2300, Revision 1, dated October 30,
2003; and Boeing Service Letter 747–SL–71–
045–C, including Attachment, dated April
10, 2003; as applicable, to perform the
actions that are required by this AD, unless
the AD specifies otherwise. The Director of
the Federal Register approves the
incorporation by reference of those
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. For copies of the
service information, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207. For
information on the availability of this
material at the National Archives and
Records Administration (NARA), call (202)
741–6030, or go to: https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html. You may view the AD
docket at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., room PL–401, Nassif
Building, Washington, DC.
Issued in Renton, Washington, on March 8,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–5298 Filed 3–18–05; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
[Docket No. FAA–2004–19535; Directorate
Identifier 2004–NM–78–AD; Amendment 39–
14020; AD 2005–06–12]
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
747–100, 747–100B, 747–100B SUD,
747–200B, 747–300, 747SP, and 747SR
series airplanes. That AD currently
requires one-time inspections for
cracking in certain upper deck floor
beams and follow-on actions. This new
AD expands the existing inspection area
and requires inspecting fastener holes in
certain areas of airplanes modified
previously, and taking corrective actions
if necessary. This action also defines
new sources for instructions for repairs
and post-modification/repair
inspections. This AD is prompted by
reports of fatigue cracking of the upper
chord of certain upper deck floor beams.
We are issuing this AD to find and fix
cracking in certain upper deck floor
beams, which could extend and sever
floor beams adjacent to the body frame
and result in rapid depressurization and
loss of controllability of the airplane.
DATES: This AD becomes effective April
25, 2005.
The incorporation by reference of
Boeing Service Bulletin 747–53A2459,
Revision 1, dated March 11, 2004, is
approved by the Director of the Federal
Register as of April 25, 2005.
On October 16, 2002 (67 FR 57510,
September 11, 2002), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 747–53A2459,
dated January 11, 2001.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
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
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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–2004–19535; the directorate
identifier for this docket is 2004–NM–
78–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: The FAA
proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR
Part 39) with an AD to supersede AD
2002–18–04, amendment 39–12878 (67
FR 57510, September 11, 2002). The
existing AD applies to certain Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–300, 747SP, and
747SR series airplanes. The proposed
AD was published in the Federal
Register on November 5, 2004 (69 FR
64525), to continue to require one-time
inspections for cracking in certain upper
deck floor beams and follow-on actions.
The proposed AD would expand the
existing inspection area, and would
require inspecting fastener holes in
certain areas of airplanes modified
previously, and taking corrective actions
if necessary. The proposed AD also
would define new sources for
instructions for repairs and postmodification/repair inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD by
a single commenter.
Request To Revise Delegation Language
The commenter requests that we
revise the proposed AD to change
references to approval of repairs or
alternative methods of compliance
(AMOCs) by Boeing Company
Designated Engineering Representatives
(DERs). The commenter states that these
provisions should refer to approval by
Authorized Representatives (ARs) of the
Boeing Delegation Option Authorization
(DOA) Organization. The commenter
notes that, since the issuance of the
proposed AD, Boeing has received a
DOA.
We concur. We have revised
paragraphs (h)(1)(i), (h)(2), and (i) of this
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
AD (which are restated requirements of
AD 2002–18–04) to delegate the
authority to approve a repair to a Boeing
Company DER or to an AR of the Boeing
DOA Organization. We have revised
paragraphs (m) and (o)(2) to delegate the
authority to approve a repair or an
AMOC to an AR of the Boeing DOA.
Request To Revise Note 2 to
Acknowledge Terminating Action
The commenter requests that we
revise Note 2 of the proposed AD, which
states:
There is no terminating action at this time
for the repetitive post-modification/repair
inspections in accordance with paragraph (i)
of this AD, and instructions for those
inspections are not provided in the original
issue of Boeing Alert Service Bulletin 747–
53A2459, dated January 11, 2001.
The commenter notes that paragraph (l)
of the proposed AD states that doing the
initial inspection required by that
paragraph terminates the repetitive
inspections required by paragraph (i).
We agree. Note 2 was carried over
with the other requirements of AD
2002–18–04. We inadvertently failed to
revise the note to reflect the fact that
inspecting in accordance with
paragraph (l) of this AD terminates the
requirements of paragraph (i) of this AD.
We have revised Note 2 of this AD to
remove the statement that there is no
terminating action for the inspections in
paragraph (i) of this AD.
Request To Revise Paragraph (j)
The commenter requests that we
clarify paragraph (j) of the proposed AD
to specify that only the holes not
previously inspected in accordance with
Boeing Alert Service Bulletin 747–
53A2459, dated January 11, 2001, need
to be inspected in accordance with that
paragraph. The commenter points out
that paragraph (g) of the proposed AD
requires modifying the upper deck floor
beams at STA 340 and STA 360. If this
modification is not done at the time of
the inspection required by paragraph (f)
of the proposed AD, paragraph (g)
specifies that the inspection in
paragraph (f) must be repeated
immediately prior to accomplishing the
modification in paragraph (g). The
commenter notes that, after the effective
date of the AD, this repeat inspection
must be accomplished in accordance
with Boeing Service Bulletin 747–
53A2459, Revision 1, dated March 11,
2004. Thus, paragraph (j) need only
require the inspection of holes not
previously inspected by the original
issue of the service bulletin.
We agree with the commenter’s
intent, but we find that no change to
this AD is necessary to meet the
commenter’s intent. Paragraph (j) of the
proposed AD already specifies doing
‘‘* * * inspections for cracking of the
fastener holes inboard of the body frame
that were not previously inspected on
the STA 340 and STA 360 upper deck
floor beams.’’ After further review,
however, we have determined that the
detailed inspection that would have
been required by paragraph (j) of this
AD is the same as the one required by
paragraph (f) of this AD. Therefore, we
have revised paragraph (j) of this AD to
remove the requirement to perform a
detailed inspection.
The commenter also requests that we
allow the inspections required by
paragraph (j) of the proposed AD to be
accomplished in accordance with Part 6
of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2459,
Revision 1. The commenter states no
rationale for its request.
We do not concur. We note that the
inspections and corrective actions
specified in Part 6 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2459, Revision
1, are applicable only to airplanes
modified in accordance with the initial
release of Boeing Alert Service Bulletin
747–53A2459. No change to the AD is
necessary in this regard.
Request To Revise Paragraph (l)
The commenter requests that we
revise paragraph (l) of the proposed AD
to acknowledge an equivalent
inspection for the purposes of
establishing the applicable compliance
time for the initial inspection specified
in Table 3 of the proposed AD. The
commenter states that an inspection in
accordance with Part 6, Figure 14, of
Boeing Service Bulletin 747–53A2459,
Revision 1, is equivalent to an
inspection in accordance with Figure 12
of Boeing Service Bulletin 747–
53A2459, Revision 1. The commenter
states that the same holes are covered by
Figure 14 and Figure 12, and the same
method is used for the inspection.
We concur, for the reasons stated by
the commenter. We have revised
paragraph (l) of this AD to specify that,
for the purposes of paragraph (l) and
Table 3 of this AD, an inspection in
accordance with Part 6, Figure 14, of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2459, Revision
1, is equivalent to an inspection in
accordance with Part 5, Figure 12, of
that service bulletin.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We have determined that these changes
will neither increase the economic
burden on any operator nor increase the
scope of the AD.
Costs of Compliance
This AD will affect about 433
airplanes worldwide. The following
table provides the estimated costs for
U.S. operators to comply with this AD.
ESTIMATED COSTS
Initial inspections (required by AD 2002–18–04) ....................................
Modification/permanent repair (required by AD 2002–18–04) ................
Post-mod/repair inspection (required by AD 2002–18–04) .....................
One-time inspection of fastener holes inboard of the body frame (new
requirement) .........................................................................................
1 Per
2 Per
Average
labor rate
per hour
Work
hours
Action
Cost per
airplane
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Fleet
cost
8
24
1 24
$65
65
65
$520
1,560
11,560
125
125
125
$65,000
195,000
1195,000
24
65
1,560
N/A
2 1,560
inspection cycle.
airplane.
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Number
of U.S.-registered airplanes
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 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 Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. 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
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–12878 (67 FR
57510, September 11, 2002), and by
adding the following new airworthiness
directive (AD):
I
2005–06–12 Boeing: Amendment 39–14020.
Docket No. FAA–2004–19535;
Directorate Identifier 2004–NM–78–AD.
Effective Date
(a) This AD becomes effective April 25,
2005.
Affected ADs
(b) This AD supersedes AD 2002–18–04,
amendment 39–12878.
Applicability
(c) This AD applies to Model 747–100,
747–100B, 747–100B SUD, 747–200B, 747–
300, 747SP, and 747SR series airplanes; line
numbers 1 through 810 inclusive; certificated
in any category; and not equipped with a
nose cargo door.
Unsafe Condition
(d) This AD was prompted by reports of
fatigue cracking of the upper chord of certain
upper deck floor beams. We are issuing this
AD to find and fix cracking in certain upper
deck floor beams, which could extend and
sever floor beams adjacent to the body frame
and result in rapid depressurization and loss
of controllability 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.
Requirements of AD 2002–18–04
Inspections
(f) At the compliance time specified in
paragraph (f)(1) or (f)(2) of this AD, as
applicable, perform one-time detailed and
open-hole high-frequency eddy current
(HFEC) inspections for cracking in the upper
deck floor beams at station (STA) 340 and
STA 360, in accordance with Boeing Alert
Service Bulletin 747–53A2459, dated January
11, 2001; or Boeing Service Bulletin 747–
53A2459, Revision 1, dated March 11, 2004.
As of the effective date of this AD, only
Revision 1 may be used. For the purposes of
this AD, flight cycles with a cabin differential
pressure of 2.0 psi or less are not calculated
into the compliance thresholds specified in
this AD. However, all cabin pressure records
must be maintained for each airplane, and no
fleet averaging of cabin pressure is allowed.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive visual
examination of a specific structural area,
system, installation, or assembly to detect
damage, failure, or irregularity. Available
lighting is normally supplemented with a
direct source of good lighting at intensity
deemed appropriate by the inspector.
Inspection aids such as mirror, magnifying
lenses, etc., may be used. Surface cleaning
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13351
and elaborate access procedures may be
required.’’
(1) For airplanes with 22,000 or fewer total
flight cycles as of October 16, 2002 (the
effective date of AD 2002–18–04): Do the
inspections prior to the accumulation of
16,000 total flight cycles, or within 1,500
flight cycles after October 16, 2002,
whichever is later.
(2) For airplanes with more than 22,000
total flight cycles as of the effective date of
this AD: Do the inspections within 500 flight
cycles after October 16, 2002.
Modification
(g) If no crack is found during the
inspections in accordance with paragraph (f)
of this AD: Within 5,000 flight cycles after
the initial inspections, modify the upper
deck floor beams at STA 340 and STA 360,
in accordance with Boeing Alert Service
Bulletin 747–53A2459, dated January 11,
2001; or Boeing Service Bulletin 747–
53A2459, Revision 1, dated March 11, 2004.
As of the effective date of this AD, only
Revision 1 may be used. If this modification
is not done before further flight after the
inspections required by paragraph (f) of this
AD, those inspections must be repeated one
time, immediately before accomplishing the
modification in this paragraph. If any crack
is found during these repeat inspections,
before further flight, accomplish paragraph
(h)(2) of this AD.
Repair
(h) If any crack is found during the
inspections in accordance with paragraph (f)
of this AD: Before further flight, repair in
accordance with either paragraph (h)(1) or
(h)(2) of this AD.
(1) Accomplish repairs in accordance with
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Accomplish a time-limited repair
(including removing certain fasteners and the
existing strap, performing open-hole HFEC
inspections of the chord and web, stopdrilling web cracks, replacing the outboard
section of the web, if applicable, and
installing new straps) in accordance with
Boeing Alert Service Bulletin 747–53A2459,
dated January 11, 2001; or Boeing Service
Bulletin 747–53A2459, Revision 1, dated
March 11, 2004; except where the service
bulletin specifies to contact Boeing for
appropriate action, repair in accordance with
a method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA; or
in accordance with data meeting the type
certification basis of the airplane approved
by a Boeing Company Designated
Engineering Representative (DER), or an
Authorized Representative (AR) for the
Boeing Delegation Option Authorization
(DOA) Organization, who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved as required by this paragraph,
the approval must specifically reference this
AD. As of the effective date of this AD, only
Revision 1 of the service bulletin may be
used.
(ii) Within 18 months or 1,500 flight cycles
after installation of the time-limited repair in
accordance with paragraph (h)(1)(i) of this
AD, whichever is first, do paragraph (h)(2) of
this AD.
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(2) Accomplish a permanent repair in
accordance with Boeing Alert Service
Bulletin 747–53A2459, dated January 11,
2001; or Boeing Service Bulletin 747–
53A2459, Revision 1, dated March 11, 2004;
except where the service bulletin specifies to
contact Boeing for appropriate action, repair
in accordance with a method approved by
the Manager, Seattle ACO; or in accordance
with data meeting the type certification basis
of the airplane approved by a Boeing
Company DER, or an AR for the Boeing DOA
Organization, who has been authorized by
the Manager, Seattle ACO, to make such
findings. For a repair method to be approved
as required by this paragraph, the approval
must specifically reference this AD. As of the
effective date of this AD, only Revision 1 of
the service bulletin may be used.
Repetitive Inspections: Post-Modification/
Repair
(i) Within 15,000 flight cycles after
modification of the upper deck floor beams
in accordance with paragraph (g) of this AD,
or after permanent repair of the upper deck
floor beams in accordance with paragraph (h)
of this AD, as applicable: Perform either
open-hole HFEC inspections for cracking of
fastener holes common to the upper chord,
reinforcement straps, and the body frame; or
surface HFEC inspections for cracking along
the lower edge of the upper chord of the floor
beam at the intersection with the body frame;
and repeat these inspections at the interval
specified in paragraph (i)(1) or (i)(2) of this
AD, as applicable, until the initial inspection
required by paragraph (l) of this AD is
complete. Perform these inspections and
repair any cracking found during these
inspections in accordance with a method
approved by the Manager, Seattle ACO, or in
accordance with data meeting the type
certification basis of the airplane approved
by a Boeing Company DER, or an AR for the
Boeing DOA Organization, who has been
authorized by the Manager, Seattle ACO, to
make such findings. For an inspection or
repair method to be approved as required by
this paragraph, the approval must
specifically reference this AD.
(1) If the most recent inspection used the
surface HFEC method: Repeat the inspection
within 1,000 flight cycles.
(2) If the most recent inspection used the
open-hole HFEC method: Repeat the
inspection every 3,000 flight cycles.
Note 2: Instructions for post-modification/
repair inspections are not provided in the
original issue of Boeing Alert Service
Bulletin 747–53A2459, dated January 11,
2001.
New Requirements of This AD
One-Time Inspection for Airplanes Inspected
Previously
(j) For airplanes on which the inspection
in paragraph (f) of this AD has been done
prior to the effective date of this AD in
accordance with Boeing Alert Service
Bulletin 747–53A2459, dated January 11,
2001, but the modification specified in
paragraph (g) or the permanent repair
specified in paragraph (h) of this AD has not
been done: At the applicable time specified
in Table 1 of this AD, do a one-time openhole HFEC inspection for cracking of the
fastener holes inboard of the body frame that
were not previously inspected on the STA
340 and STA 360 upper deck floor beams. Do
this inspection in accordance with Part 1 of
the Accomplishment Instructions of Boeing
Service Bulletin 747–53A2459, Revision 1,
dated March 11, 2004.
TABLE 1.—COMPLIANCE TIMES FOR PARAGRAPH (J)
Total number of accumulated flight
cycles as of the effective date of this AD
Compliance time
22,000 or fewer ........................................................................................
Within 5,000 flight cycles after the initial open-hole HFEC inspection for
cracking in accordance with paragraph (f) of this AD, or within 1,000
flight cycles after the effective date of this AD, whichever is later.
Prior to the accumulation of 25,000 total flight cycles, or within 1,000
flight cycles after the effective date of this AD, whichever is later.
22,001 or more .........................................................................................
One-Time Inspection for Airplanes Modified/
Repaired Previously
(k) For airplanes on which the
modification specified in paragraph (g) or the
permanent repair specified in paragraph (h)
of this AD has been done prior to the
effective date of this AD in accordance with
Boeing Alert Service Bulletin 747–53A2459,
dated January 11, 2001: At the applicable
time specified in Table 2 of this AD, do a
one-time open-hole HFEC inspection for
cracking of fastener holes common to the
modification straps, in accordance with Part
6 of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2459,
Revision 1, dated March 11, 2004.
TABLE 2.—COMPLIANCE TIMES FOR PARAGRAPH (K)
Total number of accumulated flight
cycles when the modification or permanent repair was done
Compliance time
22,000 or fewer ........................................................................................
Within 3,000 flight cycles after doing the modification or permanent repair, or 1,000 flight cycles after the effective date of this AD, whichever is later.
Within 1,500 flight cycles after doing the modification or permanent repair, or 1,000 flight cycles after the effective date of this AD, whichever is later.
22,001 or more .........................................................................................
Repetitive Inspections: Post-Modification/
Repair
(l) Do open-hole HFEC inspections for
cracking of the STA 340 and STA 360 upper
deck floor beams at fastener holes common
to the upper chord, reinforcement straps, and
body frame; or do surface HFEC inspections
for cracking along the lower edge of the
upper chord and reinforcement straps of the
floor beams. Do the applicable inspection in
accordance with Part 5 of the
Accomplishment Instructions of Boeing
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Service Bulletin 747–53A2459, Revision 1,
dated March 11, 2004. Do the initial
inspections at the applicable times specified
in Table 3 of this AD, and repeat the
inspection at the applicable interval specified
in Figure 9 of the service bulletin.
Completing the initial inspection required by
this paragraph terminates the repetitive
inspections required by paragraph (i) of this
AD. For airplanes on which paragraph (i) of
this AD has not been done, doing the initial
inspection required by this paragraph at the
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specified compliance time eliminates the
need to comply with paragraph (i) of this AD.
For the purposes of this paragraph and Table
3 of this AD, an inspection in accordance
with Part 6, Figure 14, of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2459, Revision 1, is
equivalent to an inspection in accordance
with Part 5, Figure 12, of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2459, Revision 1.
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13353
TABLE 3.—COMPLIANCE TIMES FOR INITIAL INSPECTION REQUIRED BY PARAGRAPH (L)
For the inspections identified in the following
figures referenced in Figure 9 of the service
bulletin—
Figure 10 or 11 ..................................................
Figure 10 or 11 ..................................................
Figure 10 or 11 ..................................................
Figure 12 or 13 ..................................................
Repair
(m) If any crack is found during any
inspection required by paragraph (j), (k), or
(l) of this AD: Before further flight, repair in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2459, Revision 1, dated March 11, 2004;
except where the service bulletin specifies to
contact Boeing for appropriate action, repair
in accordance with a method approved by
the Manager, Seattle ACO; or in accordance
with data meeting the type certification basis
of the airplane approved by an AR for the
Boeing DOA Organization who has been
authorized by the Manager, Seattle ACO, to
make such findings. For a repair method to
be approved, the approval must specifically
reference this AD.
Reporting Not Required
(n) Although Boeing Service Bulletin 747–
53A2459, Revision 1, dated March 11, 2004,
specifies to report certain body frame cracks
on certain airplanes, this AD does not
include that requirement.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
AR for the Boeing DOA Organization who
has been authorized by the Manager, Seattle
ACO, to make such findings.
(3) AMOCs approved previously in
accordance with AD 2002–18–04 are
approved as alternative methods of
compliance with paragraphs (f), (g), (h), and
(i) of this AD.
For these airplanes—
Do the inspection—
Airplanes not inspected previously in accordance with paragraph (i) of this AD.
Airplanes inspected previously in accordance
with paragraph (i) of this AD using the surface HFEC method for the most recent inspection.
Airplanes inspected previously in accordance
with paragraph (i) of this AD using the
open-hole HFEC method for the most recent inspection.
All airplanes ......................................................
Within 15,000 flight cycles after doing the
modification or permanent repair.
Within 1,000 flight cycles after the most recent
inspection.
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
747–53A2459, dated January 11, 2001, as of
October 16, 2002 (67 FR 57510, September
11, 2002).
(3) The Director of the Federal Register
approves the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. For copies of the
service information, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207. For
information on the availability of this
material at the National Archives and
Records Administration (NARA), call (202)
741–6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html. You may view the AD
docket at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW, room PL–401, Nassif
Building, Washington, DC.
DEPARTMENT OF TRANSPORTATION
Issued in Renton, Washington, on March 9,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–5388 Filed 3–18–05; 8:45 am]
BILLING CODE 4910–13–P
Material Incorporated by Reference
(p) You must use Boeing Alert Service
Bulletin 747–53A2459, dated January 11,
2001; or Boeing Service Bulletin 747–
53A2459, Revision 1, dated March 11, 2004;
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 747–53A2459,
Revision 1, dated March 11, 2004, in
VerDate jul<14>2003
15:51 Mar 18, 2005
Jkt 205001
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
Within 3,000 flight cycles after the most recent
inspection.
Within 6,000 flight cycles after doing the modification or permanent repair, or within 1,000
flight cycles after the effective date of this
AD, whichever is later.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19495; Directorate
Identifier 2003–NM–180–AD; Amendment
39–14019; AD 2005–06–11]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, –100B, –100B SUD,
–200B, and –300 Series Airplanes; and
Model 747SR and 747SP 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
747–100, –100B, –100B SUD, –200B,
and –300 series airplanes; and Model
747SR and 747SP series airplanes. That
AD currently requires repetitive
inspections to detect fatigue cracking in
the upper deck floor beams located at
certain body stations, and repair, if
necessary. This new AD lowers the
threshold for the existing inspections
and requires new repetitive inspections
of previously repaired areas, and repair
if necessary. This AD is prompted by
the results of an additional detailed
analysis that indicate fatigue cracks can
initiate sooner than has previously been
observed. We are issuing this AD to
prevent failure of the upper deck floor
beams at certain body stations due to
fatigue cracking, which could result in
rapid decompression and reduced
controllability of the airplane.
DATES: This AD becomes effective April
25, 2005.
E:\FR\FM\21MRR1.SGM
21MRR1
]]>Agencies
[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13349-13353]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-5388]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19535; Directorate Identifier 2004-NM-78-AD;
Amendment 39-14020; AD 2005-06-12]
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 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes. That AD
currently requires one-time inspections for cracking in certain upper
deck floor beams and follow-on actions. This new AD expands the
existing inspection area and requires inspecting fastener holes in
certain areas of airplanes modified previously, and taking corrective
actions if necessary. This action also defines new sources for
instructions for repairs and post-modification/repair inspections. This
AD is prompted by reports of fatigue cracking of the upper chord of
certain upper deck floor beams. We are issuing this AD to find and fix
cracking in certain upper deck floor beams, which could extend and
sever floor beams adjacent to the body frame and result in rapid
depressurization and loss of controllability of the airplane.
DATES: This AD becomes effective April 25, 2005.
The incorporation by reference of Boeing Service Bulletin 747-
53A2459, Revision 1, dated March 11, 2004, is approved by the Director
of the Federal Register as of April 25, 2005.
On October 16, 2002 (67 FR 57510, September 11, 2002), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 747-53A2459, dated January 11, 2001.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
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-2004-19535; the directorate
identifier for this docket is 2004-NM-78-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: The FAA proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR Part 39) with an AD to supersede
AD 2002-18-04, amendment 39-12878 (67 FR 57510, September 11, 2002).
The existing AD applies to certain Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes. The
proposed AD was published in the Federal Register on November 5, 2004
(69 FR 64525), to continue to require one-time inspections for cracking
in certain upper deck floor beams and follow-on actions. The proposed
AD would expand the existing inspection area, and would require
inspecting fastener holes in certain areas of airplanes modified
previously, and taking corrective actions if necessary. The proposed AD
also would define new sources for instructions for repairs and post-
modification/repair inspections.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD by a single commenter.
Request To Revise Delegation Language
The commenter requests that we revise the proposed AD to change
references to approval of repairs or alternative methods of compliance
(AMOCs) by Boeing Company Designated Engineering Representatives
(DERs). The commenter states that these provisions should refer to
approval by Authorized Representatives (ARs) of the Boeing Delegation
Option Authorization (DOA) Organization. The commenter notes that,
since the issuance of the proposed AD, Boeing has received a DOA.
We concur. We have revised paragraphs (h)(1)(i), (h)(2), and (i) of
this
[[Page 13350]]
AD (which are restated requirements of AD 2002-18-04) to delegate the
authority to approve a repair to a Boeing Company DER or to an AR of
the Boeing DOA Organization. We have revised paragraphs (m) and (o)(2)
to delegate the authority to approve a repair or an AMOC to an AR of
the Boeing DOA.
Request To Revise Note 2 to Acknowledge Terminating Action
The commenter requests that we revise Note 2 of the proposed AD,
which states:
There is no terminating action at this time for the repetitive
post-modification/repair inspections in accordance with paragraph
(i) of this AD, and instructions for those inspections are not
provided in the original issue of Boeing Alert Service Bulletin 747-
53A2459, dated January 11, 2001.
The commenter notes that paragraph (l) of the proposed AD states that
doing the initial inspection required by that paragraph terminates the
repetitive inspections required by paragraph (i).
We agree. Note 2 was carried over with the other requirements of AD
2002-18-04. We inadvertently failed to revise the note to reflect the
fact that inspecting in accordance with paragraph (l) of this AD
terminates the requirements of paragraph (i) of this AD. We have
revised Note 2 of this AD to remove the statement that there is no
terminating action for the inspections in paragraph (i) of this AD.
Request To Revise Paragraph (j)
The commenter requests that we clarify paragraph (j) of the
proposed AD to specify that only the holes not previously inspected in
accordance with Boeing Alert Service Bulletin 747-53A2459, dated
January 11, 2001, need to be inspected in accordance with that
paragraph. The commenter points out that paragraph (g) of the proposed
AD requires modifying the upper deck floor beams at STA 340 and STA
360. If this modification is not done at the time of the inspection
required by paragraph (f) of the proposed AD, paragraph (g) specifies
that the inspection in paragraph (f) must be repeated immediately prior
to accomplishing the modification in paragraph (g). The commenter notes
that, after the effective date of the AD, this repeat inspection must
be accomplished in accordance with Boeing Service Bulletin 747-53A2459,
Revision 1, dated March 11, 2004. Thus, paragraph (j) need only require
the inspection of holes not previously inspected by the original issue
of the service bulletin.
We agree with the commenter's intent, but we find that no change to
this AD is necessary to meet the commenter's intent. Paragraph (j) of
the proposed AD already specifies doing ``* * * inspections for
cracking of the fastener holes inboard of the body frame that were not
previously inspected on the STA 340 and STA 360 upper deck floor
beams.'' After further review, however, we have determined that the
detailed inspection that would have been required by paragraph (j) of
this AD is the same as the one required by paragraph (f) of this AD.
Therefore, we have revised paragraph (j) of this AD to remove the
requirement to perform a detailed inspection.
The commenter also requests that we allow the inspections required
by paragraph (j) of the proposed AD to be accomplished in accordance
with Part 6 of the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2459, Revision 1. The commenter states no rationale for
its request.
We do not concur. We note that the inspections and corrective
actions specified in Part 6 of the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2459, Revision 1, are applicable only to
airplanes modified in accordance with the initial release of Boeing
Alert Service Bulletin 747-53A2459. No change to the AD is necessary in
this regard.
Request To Revise Paragraph (l)
The commenter requests that we revise paragraph (l) of the proposed
AD to acknowledge an equivalent inspection for the purposes of
establishing the applicable compliance time for the initial inspection
specified in Table 3 of the proposed AD. The commenter states that an
inspection in accordance with Part 6, Figure 14, of Boeing Service
Bulletin 747-53A2459, Revision 1, is equivalent to an inspection in
accordance with Figure 12 of Boeing Service Bulletin 747-53A2459,
Revision 1. The commenter states that the same holes are covered by
Figure 14 and Figure 12, and the same method is used for the
inspection.
We concur, for the reasons stated by the commenter. We have revised
paragraph (l) of this AD to specify that, for the purposes of paragraph
(l) and Table 3 of this AD, an inspection in accordance with Part 6,
Figure 14, of the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2459, Revision 1, is equivalent to an inspection in
accordance with Part 5, Figure 12, of that service bulletin.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD will affect about 433 airplanes worldwide. The following
table provides the estimated costs for U.S. operators to comply with
this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Average Cost per U.S.-
Action Work hours labor rate airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Initial inspections (required by AD 2002-18-04) 8 $65 $520 125 $65,000
Modification/permanent repair (required by AD 24 65 1,560 125 195,000
2002-18-04)...................................
Post-mod/repair inspection (required by AD 2002- 1 24 65 11,560 125 1195,000
18-04)........................................
One-time inspection of fastener holes inboard 24 65 1,560 N/A 2 1,560
of the body frame (new requirement)...........
----------------------------------------------------------------------------------------------------------------
\1\ Per inspection cycle.
\2\ Per airplane.
[[Page 13351]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. 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 FAA amends Sec. 39.13 by removing amendment 39-12878 (67 FR
57510, September 11, 2002), and by adding the following new
airworthiness directive (AD):
2005-06-12 Boeing: Amendment 39-14020. Docket No. FAA-2004-19535;
Directorate Identifier 2004-NM-78-AD.
Effective Date
(a) This AD becomes effective April 25, 2005.
Affected ADs
(b) This AD supersedes AD 2002-18-04, amendment 39-12878.
Applicability
(c) This AD applies to Model 747-100, 747-100B, 747-100B SUD,
747-200B, 747-300, 747SP, and 747SR series airplanes; line numbers 1
through 810 inclusive; certificated in any category; and not
equipped with a nose cargo door.
Unsafe Condition
(d) This AD was prompted by reports of fatigue cracking of the
upper chord of certain upper deck floor beams. We are issuing this
AD to find and fix cracking in certain upper deck floor beams, which
could extend and sever floor beams adjacent to the body frame and
result in rapid depressurization and loss of controllability 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.
Requirements of AD 2002-18-04
Inspections
(f) At the compliance time specified in paragraph (f)(1) or
(f)(2) of this AD, as applicable, perform one-time detailed and
open-hole high-frequency eddy current (HFEC) inspections for
cracking in the upper deck floor beams at station (STA) 340 and STA
360, in accordance with Boeing Alert Service Bulletin 747-53A2459,
dated January 11, 2001; or Boeing Service Bulletin 747-53A2459,
Revision 1, dated March 11, 2004. As of the effective date of this
AD, only Revision 1 may be used. For the purposes of this AD, flight
cycles with a cabin differential pressure of 2.0 psi or less are not
calculated into the compliance thresholds specified in this AD.
However, all cabin pressure records must be maintained for each
airplane, and no fleet averaging of cabin pressure is allowed.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive visual examination of a specific structural area,
system, installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a
direct source of good lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror, magnifying lenses,
etc., may be used. Surface cleaning and elaborate access procedures
may be required.''
(1) For airplanes with 22,000 or fewer total flight cycles as of
October 16, 2002 (the effective date of AD 2002-18-04): Do the
inspections prior to the accumulation of 16,000 total flight cycles,
or within 1,500 flight cycles after October 16, 2002, whichever is
later.
(2) For airplanes with more than 22,000 total flight cycles as
of the effective date of this AD: Do the inspections within 500
flight cycles after October 16, 2002.
Modification
(g) If no crack is found during the inspections in accordance
with paragraph (f) of this AD: Within 5,000 flight cycles after the
initial inspections, modify the upper deck floor beams at STA 340
and STA 360, in accordance with Boeing Alert Service Bulletin 747-
53A2459, dated January 11, 2001; or Boeing Service Bulletin 747-
53A2459, Revision 1, dated March 11, 2004. As of the effective date
of this AD, only Revision 1 may be used. If this modification is not
done before further flight after the inspections required by
paragraph (f) of this AD, those inspections must be repeated one
time, immediately before accomplishing the modification in this
paragraph. If any crack is found during these repeat inspections,
before further flight, accomplish paragraph (h)(2) of this AD.
Repair
(h) If any crack is found during the inspections in accordance
with paragraph (f) of this AD: Before further flight, repair in
accordance with either paragraph (h)(1) or (h)(2) of this AD.
(1) Accomplish repairs in accordance with paragraphs (h)(1)(i)
and (h)(1)(ii) of this AD.
(i) Accomplish a time-limited repair (including removing certain
fasteners and the existing strap, performing open-hole HFEC
inspections of the chord and web, stop-drilling web cracks,
replacing the outboard section of the web, if applicable, and
installing new straps) in accordance with Boeing Alert Service
Bulletin 747-53A2459, dated January 11, 2001; or Boeing Service
Bulletin 747-53A2459, Revision 1, dated March 11, 2004; except where
the service bulletin specifies to contact Boeing for appropriate
action, repair in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or in accordance
with data meeting the type certification basis of the airplane
approved by a Boeing Company Designated Engineering Representative
(DER), or an Authorized Representative (AR) for the Boeing
Delegation Option Authorization (DOA) Organization, who has been
authorized by the Manager, Seattle ACO, to make those findings. For
a repair method to be approved as required by this paragraph, the
approval must specifically reference this AD. As of the effective
date of this AD, only Revision 1 of the service bulletin may be
used.
(ii) Within 18 months or 1,500 flight cycles after installation
of the time-limited repair in accordance with paragraph (h)(1)(i) of
this AD, whichever is first, do paragraph (h)(2) of this AD.
[[Page 13352]]
(2) Accomplish a permanent repair in accordance with Boeing
Alert Service Bulletin 747-53A2459, dated January 11, 2001; or
Boeing Service Bulletin 747-53A2459, Revision 1, dated March 11,
2004; except where the service bulletin specifies to contact Boeing
for appropriate action, repair in accordance with a method approved
by the Manager, Seattle ACO; or in accordance with data meeting the
type certification basis of the airplane approved by a Boeing
Company DER, or an AR for the Boeing DOA Organization, who has been
authorized by the Manager, Seattle ACO, to make such findings. For a
repair method to be approved as required by this paragraph, the
approval must specifically reference this AD. As of the effective
date of this AD, only Revision 1 of the service bulletin may be
used.
Repetitive Inspections: Post-Modification/Repair
(i) Within 15,000 flight cycles after modification of the upper
deck floor beams in accordance with paragraph (g) of this AD, or
after permanent repair of the upper deck floor beams in accordance
with paragraph (h) of this AD, as applicable: Perform either open-
hole HFEC inspections for cracking of fastener holes common to the
upper chord, reinforcement straps, and the body frame; or surface
HFEC inspections for cracking along the lower edge of the upper
chord of the floor beam at the intersection with the body frame; and
repeat these inspections at the interval specified in paragraph
(i)(1) or (i)(2) of this AD, as applicable, until the initial
inspection required by paragraph (l) of this AD is complete. Perform
these inspections and repair any cracking found during these
inspections in accordance with a method approved by the Manager,
Seattle ACO, or in accordance with data meeting the type
certification basis of the airplane approved by a Boeing Company
DER, or an AR for the Boeing DOA Organization, who has been
authorized by the Manager, Seattle ACO, to make such findings. For
an inspection or repair method to be approved as required by this
paragraph, the approval must specifically reference this AD.
(1) If the most recent inspection used the surface HFEC method:
Repeat the inspection within 1,000 flight cycles.
(2) If the most recent inspection used the open-hole HFEC
method: Repeat the inspection every 3,000 flight cycles.
Note 2: Instructions for post-modification/repair inspections
are not provided in the original issue of Boeing Alert Service
Bulletin 747-53A2459, dated January 11, 2001.
New Requirements of This AD
One-Time Inspection for Airplanes Inspected Previously
(j) For airplanes on which the inspection in paragraph (f) of
this AD has been done prior to the effective date of this AD in
accordance with Boeing Alert Service Bulletin 747-53A2459, dated
January 11, 2001, but the modification specified in paragraph (g) or
the permanent repair specified in paragraph (h) of this AD has not
been done: At the applicable time specified in Table 1 of this AD,
do a one-time open-hole HFEC inspection for cracking of the fastener
holes inboard of the body frame that were not previously inspected
on the STA 340 and STA 360 upper deck floor beams. Do this
inspection in accordance with Part 1 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2459, Revision 1,
dated March 11, 2004.
Table 1.--Compliance Times for Paragraph (j)
------------------------------------------------------------------------
Total number of accumulated flight
cycles as of the effective date of this Compliance time
AD
------------------------------------------------------------------------
22,000 or fewer........................ Within 5,000 flight cycles
after the initial open-hole
HFEC inspection for cracking
in accordance with paragraph
(f) of this AD, or within
1,000 flight cycles after the
effective date of this AD,
whichever is later.
22,001 or more......................... Prior to the accumulation of
25,000 total flight cycles, or
within 1,000 flight cycles
after the effective date of
this AD, whichever is later.
------------------------------------------------------------------------
One-Time Inspection for Airplanes Modified/Repaired Previously
(k) For airplanes on which the modification specified in
paragraph (g) or the permanent repair specified in paragraph (h) of
this AD has been done prior to the effective date of this AD in
accordance with Boeing Alert Service Bulletin 747-53A2459, dated
January 11, 2001: At the applicable time specified in Table 2 of
this AD, do a one-time open-hole HFEC inspection for cracking of
fastener holes common to the modification straps, in accordance with
Part 6 of the Accomplishment Instructions of Boeing Service Bulletin
747-53A2459, Revision 1, dated March 11, 2004.
Table 2.--Compliance Times for Paragraph (k)
------------------------------------------------------------------------
Total number of accumulated flight
cycles when the modification or Compliance time
permanent repair was done
------------------------------------------------------------------------
22,000 or fewer........................ Within 3,000 flight cycles
after doing the modification
or permanent repair, or 1,000
flight cycles after the
effective date of this AD,
whichever is later.
22,001 or more......................... Within 1,500 flight cycles
after doing the modification
or permanent repair, or 1,000
flight cycles after the
effective date of this AD,
whichever is later.
------------------------------------------------------------------------
Repetitive Inspections: Post-Modification/Repair
(l) Do open-hole HFEC inspections for cracking of the STA 340
and STA 360 upper deck floor beams at fastener holes common to the
upper chord, reinforcement straps, and body frame; or do surface
HFEC inspections for cracking along the lower edge of the upper
chord and reinforcement straps of the floor beams. Do the applicable
inspection in accordance with Part 5 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2459, Revision 1,
dated March 11, 2004. Do the initial inspections at the applicable
times specified in Table 3 of this AD, and repeat the inspection at
the applicable interval specified in Figure 9 of the service
bulletin. Completing the initial inspection required by this
paragraph terminates the repetitive inspections required by
paragraph (i) of this AD. For airplanes on which paragraph (i) of
this AD has not been done, doing the initial inspection required by
this paragraph at the specified compliance time eliminates the need
to comply with paragraph (i) of this AD. For the purposes of this
paragraph and Table 3 of this AD, an inspection in accordance with
Part 6, Figure 14, of the Accomplishment Instructions of Boeing
Service Bulletin 747-53A2459, Revision 1, is equivalent to an
inspection in accordance with Part 5, Figure 12, of the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2459,
Revision 1.
[[Page 13353]]
Table 3.--Compliance Times for Initial Inspection Required By
Paragraph(l)
------------------------------------------------------------------------
For the inspections identified
in the following figures For these Do the inspection--
referenced in Figure 9 of the airplanes--
service bulletin--
------------------------------------------------------------------------
Figure 10 or 11................. Airplanes not Within 15,000
inspected flight cycles
previously in after doing the
accordance with modification or
paragraph (i) of permanent repair.
this AD.
Figure 10 or 11................. Airplanes Within 1,000
inspected flight cycles
previously in after the most
accordance with recent
paragraph (i) of inspection.
this AD using the
surface HFEC
method for the
most recent
inspection.
Figure 10 or 11................. Airplanes Within 3,000
inspected flight cycles
previously in after the most
accordance with recent
paragraph (i) of inspection.
this AD using the
open-hole HFEC
method for the
most recent
inspection.
Figure 12 or 13................. All airplanes..... Within 6,000
flight cycles
after doing the
modification or
permanent repair,
or within 1,000
flight cycles
after the
effective date of
this AD,
whichever is
later.
------------------------------------------------------------------------
Repair
(m) If any crack is found during any inspection required by
paragraph (j), (k), or (l) of this AD: Before further flight, repair
in accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2459, Revision 1, dated March 11, 2004; except where
the service bulletin specifies to contact Boeing for appropriate
action, repair in accordance with a method approved by the Manager,
Seattle ACO; or in accordance with data meeting the type
certification basis of the airplane approved by an AR for the Boeing
DOA Organization who has been authorized by the Manager, Seattle
ACO, to make such findings. For a repair method to be approved, the
approval must specifically reference this AD.
Reporting Not Required
(n) Although Boeing Service Bulletin 747-53A2459, Revision 1,
dated March 11, 2004, specifies to report certain body frame cracks
on certain airplanes, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an AR
for the Boeing DOA Organization who has been authorized by the
Manager, Seattle ACO, to make such findings.
(3) AMOCs approved previously in accordance with AD 2002-18-04
are approved as alternative methods of compliance with paragraphs
(f), (g), (h), and (i) of this AD.
Material Incorporated by Reference
(p) You must use Boeing Alert Service Bulletin 747-53A2459,
dated January 11, 2001; or Boeing Service Bulletin 747-53A2459,
Revision 1, dated March 11, 2004; 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 747-53A2459,
Revision 1, dated March 11, 2004, 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-
53A2459, dated January 11, 2001, as of October 16, 2002 (67 FR
57510, September 11, 2002).
(3) The Director of the Federal Register approves the
incorporation by reference of these documents in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. For copies of the service
information, contact Boeing Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124-2207. For information on the availability
of this material at the National Archives and Records Administration
(NARA), call (202) 741-6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html. You may view the AD docket at the Docket Management
Facility, U.S. Department of Transportation, 400 Seventh Street SW,
room PL-401, Nassif Building, Washington, DC.
Issued in Renton, Washington, on March 9, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-5388 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P
