Airworthiness Directives; The Boeing Company Model 747 Airplanes, 8279-8285 [2010-3542]
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Federal Register / Vol. 75, No. 36 / Wednesday, February 24, 2010 / Proposed Rules
Commission Secretary, at (202) 694–
1040, at least 72 hours prior to the
hearing date.
On behalf of the Commission,
Dated: February 18, 2010.
Matthew S. Petersen,
Chairman, Federal Election Commission.
[FR Doc. 2010–3639 Filed 2–23–10; 8:45 am]
BILLING CODE 6715–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0981; Directorate
Identifier 2008–NM–073–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747 Airplanes
cprice-sewell on DSK2BSOYB1PROD with PROPOSALS
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
SUMMARY: The FAA is revising an earlier
NPRM for an airworthiness directive
(AD) that applies to certain Model 747
airplanes. The original NPRM would
have superseded an existing AD that
currently requires repetitive inspections
of the body station (BS) 2598 bulkhead,
and corrective actions if necessary. The
existing AD also currently requires a
terminating modification for the
repetitive inspections and a postmodification inspection of the modified
area. The original NPRM proposed to
continue to require those actions using
revised service information. For certain
airplanes, the original NPRM proposed
to require new repetitive inspections, an
interim modification, and post-interim
modification inspections. For certain
airplanes, the original NPRM also
proposed to require replacing any
previously repaired aft inner chord and
reinstalling the terminating
modification. The original NPRM
resulted from reports of cracked aft
inner chords on airplanes after certain
requirements of the existing AD were
done. This new action revises the
original NPRM for airplanes that are
converted to the Model 747–400 large
cargo freighter (LCF) configuration by
reducing the threshold and repeat
intervals of certain post-modification
inspections. This new action also
revises the original NPRM for all
airplanes by proposing that certain
inspections of the upper aft outer chords
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and diagonal brace attachment fittings,
flanges, and rods continue after the
terminating modification. We are
proposing this supplemental NPRM to
prevent fatigue cracking of the BS 2598
bulkhead structure, which could result
in inability of the structure to carry
horizontal stabilizer flight loads, and
loss of controllability of the airplane.
DATES: We must receive comments on
this supplemental NPRM by March 22,
2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221 or 425–227–1152.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6437;
fax (425) 917–6590.
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8279
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0981; Directorate Identifier
2008–NM–073–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR
part 39) with a notice of proposed
rulemaking (NPRM) for an AD (the
‘‘original NPRM’’) to supersede AD
2006–05–06, amendment 39–14503 (71
FR 12125, March 9, 2006). The original
NPRM applied to certain Model 747
airplanes. The original NPRM was
published in the Federal Register on
September 23, 2008 (73 FR 54751). The
original NPRM proposed to require
repetitive inspections of the body
station (BS) 2598 bulkhead, and
corrective actions if necessary; and a
terminating modification for the
repetitive inspections and a postmodification inspection of the modified
area. The original NPRM proposed to
require those actions using revised
service information. For certain
airplanes, the original NPRM proposed
to require new repetitive inspections, an
interim modification, and post-interim
modification inspections. For certain
airplanes, the original NPRM also
proposed to require replacing any
previously repaired aft inner chord and
reinstalling the terminating
modification.
Actions Since Original NPRM was
Issued
Since we issued the original NPRM,
Boeing informed us that the compliance
times of certain post-modification
inspections need to be revised for Model
747–400 series airplanes that have been
modified to operate in a freighter
configuration. These airplanes are
referred to as large cargo freighters, or
LCF. Boeing states that higher operating
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stresses for the subject structure on the
Model 747–400 LCF airplanes mean that
these airplanes need a lower inspection
threshold and shorter repeat intervals
than those specified in the original
NPRM. We agree, and we have revised
paragraphs (m), (q), and (r) of the
original NPRM to reduce the threshold
and repetitive intervals.
In addition, Boeing informed us that
for all airplanes certain inspections of
the upper aft outer chords and diagonal
brace attachment fittings, flanges, and
rods need to be continued after the
terminating modification is
accomplished. Adding the reinforcing
modification and replacing the aft inner
chord as specified in the NPRM does
not alter the upper aft outer chord and
diagonal brace attachment fittings,
flanges, and rods. Therefore, we have
revised paragraph (q) of the original
NPRM to specify that certain
inspections must continue after the
terminating modification.
Comments
We have considered the following
comments on the original NPRM.
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Request To Revise Costs of Compliance
Northwest Airlines requests that we
revise the ‘‘Costs of Compliance’’ section
of the original NPRM to include
Boeing’s current cost of the modification
kit. Northwest Airlines states that the
current cost is $52,218 rather than the
$33,716 quoted in the original NPRM.
We agree that the cost of the
modification kit has changed. We have
revised the ‘‘Costs of Compliance’’
section of this supplemental NPRM to
include the new cost of the kit.
Request To Delay the AD Pending
Revised Service Information
All Nippon Airways and Japan
Airlines request that we delay issuing
the AD until Boeing revises Alert
Service Bulletin 747–53A2427 to
Revision 5 (we referred to Boeing Alert
Service Bulletin 747–53A2427, Revision
4, dated March 6, 2008, in the original
NPRM). All Nippon Airways explains
that it has discussed several
discrepancies in Revision 4 with
Boeing, and that Boeing clarified those
discrepancies in an information notice
(IN). All Nippon Airways states that,
since INs are not approved by the FAA,
it will be a burden to operators to
request alternative methods of
compliance (AMOCs) once the proposed
rule is mandated. As an alternative, All
Nippon Airways proposes that we
include the additional information from
the IN in the final rule.
In addition, Boeing has informed us
that there is a discrepancy in the
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modification drawing specified in
Boeing Alert Service Bulletin 747–
53A2427, Revision 4, dated March 6,
2008. The drawing does not include a
step to ‘‘zero-time’’ certain existing
fastener holes in the affected areas. The
zero-timing is intended to remove any
undetectable cracks in the affected
fastener holes.
We agree that we should refer to the
most recent service information
possible. We have reviewed Boeing
Service Bulletin 747–53A2427, Revision
5, dated October 1, 2009. The revised
service information includes the
information in the IN referred to by the
commenter (the IN clarifies fastener
codes and repair instructions) and does
not require any additional work on
airplanes on which the inspections,
interim modification, and repair
specified in earlier revisions of the
service bulletin were done. Therefore,
we have revised paragraphs (i), (j), (o),
(s), (t), (u), and (v) of this supplemental
NPRM to refer to Boeing Service
Bulletin 747–53A2427, Revision 5,
dated October 1, 2009. We have also
added new paragraph (w) to the
supplemental NPRM to give credit for
doing certain actions in accordance with
Boeing Alert Service Bulletin 747–
53A2427, Revision 4, dated March 6,
2008.
We have also reviewed Boeing Service
Bulletin 747–53–2473, Revision 1, dated
February 20, 2007; and Boeing Alert
Service Bulletin 747–53A2473, Revision
2, dated August 28, 2009. We referred to
Boeing Service Bulletin 747–53–2473,
dated March 24, 2005, as the
appropriate source of service
information for accomplishing the
required actions specified in paragraph
(m) of the NPRM.
Boeing Service Bulletin 747–53–2473,
Revision 1, dated February 20, 2007,
retains and clarifies the same
procedures as in Boeing Service Bulletin
747–53–2473, dated March 24, 2005,
and adds procedures to replace repaired
aft inner chords on certain airplanes on
which the actions specified in Boeing
Service Bulletin 747–53–2473, dated
March 24, 2005, were done.
Boeing Alert Service Bulletin 747–
53A2473, Revision 2, dated August 28,
2009, adds procedures to inspect to
determine if certain fasteners were
installed, and to do related investigative
and corrective actions if necessary, for
airplanes on which the support frame
modification specified in Boeing Service
Bulletin 747–53–2473, dated March 24,
2005; or Revision 1, dated February 20,
2007; was done. The related
investigative actions include an openhole high frequency eddy current
(HFEC) inspection of the fastener holes
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of a certain type of fastener for cracks,
and a review of maintenance records to
verify that an open-hole HFEC
inspection was performed at certain
other fastener holes and the holes were
zero-timed. For airplanes on which the
holes were not zero-timed, the service
bulletin specifies an HFEC inspection of
the holes for cracks, and corrective
actions if necessary. Boeing Alert
Service Bulletin 747–53A2473, Revision
2, dated August 28, 2009, also adds
procedures to do post-modification
inspections.
We have revised paragraph (m) of this
supplemental NPRM to refer to Boeing
Service Bulletin 747–53–2473, Revision
1, dated February 20, 2007; and Boeing
Alert Service Bulletin 747–53A2473,
Revision 2, dated August 28, 2009. We
have revised paragraph (q) of this
supplemental NPRM to refer to Boeing
Alert Service Bulletin 747–53A2473,
Revision 2, dated August 28, 2009.
We have also revised paragraphs (n)
and (r) of this supplemental NPRM to
refer to Boeing Alert Service Bulletin
747–53A2473, Revision 2, dated August
28, 2009, for the post-modification
inspections.
Explanation of Change to Paragraph (r)
of This Supplemental NPRM
Boeing Alert Service Bulletin 747–
53A2473, Revision 2, dated August 28,
2009, also adds procedures for postmodification inspections. In paragraph
(r) of the NPRM, we specified doing a
post-modification inspection for
cracking and repair of any crack, in
accordance with a method approved by
the FAA. Because Boeing Service
Bulletin 747–53A2473, Revision 2,
dated August 28, 2009, specifies doing
support frame post-modification
inspections, we have revised paragraph
(r) of this supplemental NPRM to refer
to that service bulletin. The support
frame post-modification inspections
consist of the following inspections
specified in Parts 1, 2, and 3 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 747–53A2473,
Revision 2, dated August 28, 2009.
The ‘‘Part 1—Support Frame
Inspections’’ include the following
inspections:
• A detailed inspection for cracking
of the support frame and access cut-out
forward and aft sides at station 2598.
• A surface HFEC inspection for
cracking of the lower floor support
chord at station 2598.
• A low frequency eddy current
(LFEC) inspection for cracking of the
support frame outer chord at station
2598.
• A surface and open-hole HFEC
inspection for cracking of the support
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frame outer chord and fitting at station
2598.
• An ultrasonic or surface HFEC
inspection for cracking of the support
frame outer chord at station 2598.
The ‘‘Part 2—Hinge Support
Inspection’’ is an open-hole HFEC
inspection for cracking in the back-up
fittings, frame support fitting and hinge
fitting at station 2598.
The ‘‘Part 3—Support Frame
Inspections’’ include the following
inspections:
• Detailed inspections for cracking of
the frame web around the periphery of
the aft inner chord and the entire
modified support frame.
• Surface HFEC inspections for
cracking in the upper forward inner
chord, aft inner chord, upper splice
fitting, lower forward inner chord, and
frame support fitting, lower splice
fitting, hinge frame support fitting.
• An LFEC or open-hole HFEC for
cracking in the upper aft inner chord.
• Ultrasonic inspections for cracking
in the upper and lower forward inner
chord and frame support fitting.
• A surface HFEC inspection for
cracking of the frame web.
• An LFEC for cracking in the aft
outer chord.
If any cracking is found, the service
bulletin specifies the corrective action
as contacting Boeing for repair data and
doing the repair.
Boeing Alert Service Bulletin 747–
53A2473, Revision 2, dated August 28,
2009, specifies that the initial
compliance times for doing support
frame post-modification inspections
ranges between within 1,500 flight
cycles after doing the modification to
within 20,000 flight cycles after doing
the modification, depending on the
inspection and airplane configuration.
The service bulletin specifies that the
repetitive interval for the support frame
post-modification inspections ranges
between 1,000 flight cycles and 6,000
flight cycles, depending on the
inspection.
Explanation of New Compliance Time
for Certain Airplanes in Paragraph (m)
of This Supplemental NPRM
For airplanes that are modified as
specified in paragraph (m) of the
supplemental NPRM and are converted
to the Model 747–400 Large Cargo
Freighter (LCF) configuration, the
repetitive inspection specified in
paragraph (k)(2) of this AD must be
done thereafter at intervals not to
exceed 1,800 flight cycles. We have
revised paragraph (m) of this AD
accordingly.
Clarification of Compliance Time
We have revised paragraph (q)(2) of
this supplemental NPRM to specify that
the applicable related investigative and
corrective actions must be done before
further flight, as specified in Boeing
Alert Service Bulletin 747–53A2473,
Revision 2, dated August 28, 2009.
Explanation of Change Made to
Paragraph (x)(3) of This Supplemental
NPRM
Boeing Commercial Airplanes has
received an Organization Designation
Authorization (ODA), which replaces
their previous designation as a
Delegation Option Authorization (DOA)
holder. We have revised paragraph
(x)(3) of this AD to delegate the
authority to approve an alternative
method of compliance for any repair
required by this AD to the Boeing
Commercial Airplanes ODA.
Explanation of Added/Removed
Paragraphs in the Supplemental NPRM
We have added a new paragraph (d)
to this supplemental NPRM to provide
the Air Transport Association (ATA) of
America subject code for this proposed
AD. This code is added to make this
supplemental NPRM parallel with other
new AD actions. We have re-identified
subsequent paragraphs accordingly.
Paragraph (n) of the original NPRM
indicates that, after the effective date of
the AD, Boeing Alert Service Bulletin
8281
747–53A2427, Revision 4, dated March
6, 2008, must be used to accomplish the
requirements of paragraphs (h) and (i) of
the original NPRM (i.e., paragraphs (i)
and (j) of this supplemental NPRM). We
have removed paragraph (n) of the
original NPRM, and have referred to
Boeing Service Bulletin 747–53A2427,
Revision 5, dated October 1, 2009, in
paragraphs (i) and (j) of this
supplemental NPRM.
Explanation of Additional Change to
‘‘Costs of Compliance’’ Paragraph
We have revised the ‘‘Costs of
Compliance’’ section to clarify which
costs are retained from AD 2006–05–06
and which costs are new in this
supplemental NPRM.
Explanation of Changes Made to the
Manufacturer Name
We have revised this supplemental
NPRM to identify the legal name of the
manufacturer as published in the most
recent type certificate data sheet for the
affected airplane models.
FAA’s Determination and Proposed
Requirements of the Supplemental
NPRM
We are proposing this supplemental
NPRM because we evaluated all
pertinent information and determined
an unsafe condition exists and is likely
to exist or develop on other products of
the same type design. Certain changes
described above expand the scope of the
original NPRM. As a result, we have
determined that it is necessary to reopen
the comment period to provide
additional opportunity for the public to
comment on this supplemental NPRM.
Costs of Compliance
There are about 998 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD. The
average labor rate is $80 per work hour.
ESTIMATED COSTS
Work
hours
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Action
Surface HFEC inspections (required by AD 2006-05-06) and
open-hole HFEC inspections
(new proposed action).
Detailed inspections (required by
AD 2006-05-06).
Terminating modification (partially
required by AD 2006-05-06; additional modification actions in
this new proposed action).
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15:10 Feb 23, 2010
Parts
Cost per airplane
Number of
U.S.registered
airplanes
Fleet cost
2
None
$160, per inspection cycle ...........
162
$25,920, per inspection cycle.
2
None
$160, per inspection cycle ...........
162
$25,920, per inspection cycle.
126
$52,218
$62,298 ........................................
162
$10,092,276.
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Federal Register / Vol. 75, No. 36 / Wednesday, February 24, 2010 / Proposed Rules
ESTIMATED COSTS—Continued
Work
hours
Action
Interim modification (new proposed action).
Replacement of previously repaired aft inner chords (new
proposed action).
Support Frame upper Corner
Fastener Inspection (new proposed action).
Post-modification inspection (new
proposed action).
Parts
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Fleet cost
4,000
$4,320 ..........................................
162
$699,840.
2
None
$160 .............................................
162
$25,920.
8
None
$640 .............................................
162
$103,680.
4
None
$320 .............................................
162
$51,840.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this supplemental NPRM and placed it
15:10 Feb 23, 2010
Number of
U.S.registered
airplanes
4
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.
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Cost per airplane
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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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14503 (71
FR 12125, March 9, 2006) and adding
the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA–
2008–0981; Directorate Identifier 2008–
NM–073–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by March 22, 2010.
Affected ADs
(b) This AD supersedes AD 2006–05–06,
Amendment 39–14503.
Applicability
(c) This AD applies to The Boeing
Company Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–400F,
747SR, and 747SP series airplanes,
certificated in any category, line numbers 1
though 1307 inclusive.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
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(e) This AD results from reports of cracked
aft inner chords on airplanes after certain
requirements of the existing AD were done.
We are issuing this AD to prevent fatigue
cracking of the body station (BS) 2598
bulkhead structure, which could result in
inability of the structure to carry horizontal
stabilizer flight loads, and loss of
controllability of the airplane.
Compliance
(f) 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 2006–
05–06
1. The authority citation for part 39
continues to read as follows:
§ 39.13
Unsafe Condition
Repetitive High Frequency Eddy Current
(HFEC) Inspections of the Bulkhead Frame
Supports
(g) Before the accumulation of 10,000 total
flight cycles, or within 1,000 flight cycles
after August 16, 2001 (the effective date of
AD 2001–14–07, amendment 39–12318,
which was superseded by AD 2006–05–06),
whichever occurs later: Do an open-hole
HFEC inspection to find cracking of the
bulkhead frame support under the hinge
support fittings of the horizontal stabilizer on
the left and right sides at BS 2598, in
accordance with Figure 2 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2449, Revision 1,
dated May 24, 2001; or Revision 2, dated
March 14, 2002. Repeat the inspection after
that at intervals not to exceed 3,000 flight
cycles. Inspections accomplished before
August 16, 2001, per Boeing Alert Service
Bulletin 747–53A2449, dated June 8, 2000,
are considered acceptable for compliance
with the applicable inspection specified in
this paragraph.
Repair of Any Cracked Bulkhead Frame
Support
(h) If any cracking is found during any
inspection required by paragraph (g) of this
AD, before further flight, repair using a
method approved in accordance with the
procedures specified in paragraph (x) of this
AD.
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Repetitive Inspections of Inner Chords,
Frame Support Fitting, and Splice Fitting
(i) Do a surface HFEC inspection of the
forward and aft inner chords, the frame
support, and the splice fitting of the forward
inner chord of the upper corners of the
station 2598 bulkhead to find cracking, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2427, Revision 2, dated October 5,
2000; Revision 3, dated September 27, 2001;
or Boeing Service Bulletin 747–53A2427,
Revision 5, dated October 1, 2009; at the
latest of the times specified in paragraphs
(i)(1) and (i)(2) of this AD, as applicable.
Repeat the inspection after that at intervals
not to exceed 1,500 flight cycles. After the
effective date of this AD, Boeing Service
Bulletin 747–53A2427, Revision 5, dated
October 1, 2009, must be used.
(1) For airplanes having line numbers 1
through 1241 inclusive:
(i) Before the accumulation of 6,000 total
flight cycles.
(ii) Within 500 flight cycles after August
28, 2001 (the effective date of AD 2001–15–
03, amendment 39–12337, which was
superseded by AD 2006–05–06).
(iii) For airplanes inspected before August
28, 2001, in accordance with Boeing Alert
Service Bulletin 747–53A2427, dated
December 17, 1998 (including inspections of
the splice fitting); or Revision 1, dated
October 28, 1999: Within 1,500 flight cycles
after accomplishment of the last inspection
done in accordance with the original service
bulletin or Revision 1, as applicable.
(2) For airplanes having line numbers 1242
through 1307 inclusive:
(i) Before the accumulation of 16,000 total
flight cycles.
(ii) Within 500 flight cycles after August
28, 2001.
(iii) For airplanes inspected before August
28, 2001, in accordance with Boeing Alert
Service Bulletin 747–53A2427, dated
December 17, 1998 (including inspections of
the splice fitting), or Revision 1, dated
October 28, 1999: Within 1,500 flight cycles
after accomplishment of the last inspection
done in accordance with Boeing Alert
Service Bulletin 747–53A2427, dated
December 17, 1998; or Revision 1, dated
October 28, 1999, as applicable.
Repair of Any Cracked Inner Chord, Frame
Support, or Splice Fitting
(j) If any cracking is found during the
inspections required by paragraph (i) of this
AD, before further flight, repair in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2427,
Revision 2, dated October 5, 2000; Revision
3, dated September 27, 2001; or Boeing
Service Bulletin 747–53A2427, Revision 5,
dated October 1, 2009. After the effective
date of this AD, Boeing Service Bulletin 747–
53A2427, Revision 5, dated October 1, 2009,
must be used. Where Boeing Alert Service
Bulletin 747–53A2427, Revision 2, dated
October 5, 2000; Revision 3, dated September
27, 2001; or Boeing Service Bulletin 747–
53A2427, Revision 5, dated October 1, 2009;
specifies that the manufacturer may be
contacted for disposition of certain repair
conditions, before further flight, repair using
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15:10 Feb 23, 2010
Jkt 220001
a method approved in accordance with the
procedures specified in paragraph (x) of this
AD.
Repetitive Detailed Inspections of BS 2598
Bulkhead
(k) Before the accumulation of 10,000 total
flight cycles, or within 1,000 flight cycles
after October 27, 2003 (the effective date of
AD 2003–19–08, amendment 39–13311,
which was superseded by AD 2006–05–06),
whichever is later: Do a detailed inspection
of the BS 2598 bulkhead for discrepancies
(cracking, elongated fastener holes) of the
areas specified in paragraphs (k)(1) and (k)(2)
of this AD, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2467, dated July 26,
2001; or Revision 1, dated April 28, 2005.
Repeat the inspections after that at intervals
not to exceed 3,000 flight cycles, except as
required by paragraph (m) of this AD. Doing
the modification specified in paragraph (m)
or (q) of this AD terminates the inspection of
the area specified in paragraph (k)(1) of this
AD.
(1) The lower aft inner chords.
(2) The upper aft outer chords, and the
diagonal brace attachment fittings, flanges,
and rods.
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 mirrors magnifying
lenses, etc. may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Repair of Any Cracked BS 2598 Bulkhead
(l) If any discrepancy is found during any
inspection required by paragraph (k) of this
AD: Before further flight, repair in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2467, dated July 26, 2001; or
Revision 1, dated April 28, 2005. If the
service bulletin specifies to contact Boeing
for appropriate action: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (x) of this AD.
Terminating Modification With New
Compliance Time for Certain Airplanes for
the Inspection Specified in Paragraph (k)(2)
of This AD
(m) Except as provided by paragraph (q) of
this AD: Before the accumulation of 20,000
total flight cycles, or within 48 months after
April 13, 2006 (the effective date of AD
2006–05–06), whichever occurs later, modify
the bulkhead by doing all applicable actions
including surface and open-hole HFEC
inspections for cracking of the upper forward
inner chords, aft inner chords, upper splice
fittings, and frame support fittings, as
specified in the Accomplishment
Instructions of Boeing Service Bulletin 747–
53–2473, dated March 24, 2005; Revision 1,
dated February 20, 2007; or Boeing Alert
Service Bulletin 747–53A2473, Revision 2,
dated August 28, 2009. Repair any cracks
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8283
before further flight, in accordance with
Boeing Service Bulletin 747–53–2473, dated
March 24, 2005; Revision 1, dated February
20, 2007; or Boeing Alert Service Bulletin
747–53A2473, Revision 2, dated August 28,
2009. Where Boeing Service Bulletin 747–
53–2473, dated March 24, 2005; Revision 1,
dated February 20, 2007; or Boeing Alert
Service Bulletin 747–53A2473, Revision 2,
dated August 28, 2009 specifies that the
manufacturer may be contacted for
disposition of certain repair conditions:
Before further flight, repair the cracks using
a method approved in accordance with the
procedures specified in paragraph (x) of this
AD. Accomplishment of the modification
terminates the requirements of paragraphs
(g), (i), and (k)(1) of this AD. After the
effective date of this AD, Boeing Alert
Service Bulletin 747–53A2473, Revision 2,
dated August 28, 2009 must be used for the
actions specified in this paragraph. For
airplanes that are converted to the Model
747–400 Large Cargo Freighter (LCF)
configuration, repeat the inspection specified
in paragraph (k)(2) of this AD thereafter at
intervals not to exceed 1,800 flight cycles.
Post-Modification Inspection and Repair
(n) Except as provided by paragraphs (q)
and (r) of this AD: Within 20,000 flight cycles
after doing the modification required by
paragraph (m) of this AD, inspect the BS
2598 bulkhead for cracks, and repair any
cracks before further flight, in accordance
with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO).
New Requirements of This AD
Terminating Repair for Repetitive Surface
HFEC Inspections
(o) As of the effective date of this AD,
accomplishing the aft inner chord repair
required by paragraph (j) of this AD in
accordance with the applicable structural
repair manual (SRM) specified in the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2427, Revision 5,
dated October 1, 2009, ends the repetitive
surface HFEC inspections required by
paragraph (i) of this AD for that side of the
bulkhead only.
Replacement of Previously Repaired Aft
Inner Chord and Reinstallation of
Terminating Modification
(p) For airplanes on which the terminating
modification required by paragraph (m) of
this AD has been done in accordance with
Boeing Service Bulletin 747–53–2473, dated
March 24, 2005: Within 1,500 flight cycles
after doing the modification, or within 1,000
flight cycles after the effective date of this
AD, whichever occurs later, do a one-time
general visual inspection for repairs installed
previously on the left and right side aft inner
chords. For airplanes with previously
installed repairs, before further flight, do
rework (i.e., replace any previously repaired
aft inner chord with a new aft inner chord
and reinstall the terminating modification),
using a method approved in accordance with
the procedures specified in paragraph (x) of
this AD.
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Revised Terminating Modification
(q) Doing the applicable modification
required by paragraph (q)(1) or (q)(2) of this
AD at the applicable time terminates the
requirements of paragraph (m) of this AD and
the repetitive inspections required by
paragraphs (g), (i), and (k)(1) of this AD. For
airplanes that are converted to the Model
747–400 LCF configuration, the inspection
specified in paragraph (k)(2) of this AD must
be repeated thereafter at intervals not to
exceed 1,800 flight cycles.
(1) For airplanes on which the terminating
modification required by paragraph (m) of
this AD has not been done as of the effective
date of this AD: Before the accumulation of
20,000 total flight cycles, or within 18
months after the effective date of this AD,
whichever occurs later, modify the bulkhead,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2473, Revision 2, dated August 28,
2009; except that where Boeing Alert Service
Bulletin 747–53A2473, Revision 2, dated
August 28, 2009, specifies to contact Boeing
for modification data, the modification data
must be approved in accordance with the
procedures specified in paragraph (x) of this
AD and the modification must be done
within the times specified in this paragraph.
(2) For airplanes on which the terminating
modification required by paragraph (m) of
this AD has been done in accordance with
Boeing Service Bulletin 747–53–2473, dated
March 24, 2005; or Revision 1, dated
February 20, 2007; as of the effective date of
this AD: Within 1,000 flight cycles after the
effective date of this AD, or within 1,500
flight cycles after doing the modification,
whichever occurs later, do a general visual
inspection of the applicable areas specified
in paragraphs (q)(2)(i) and (q)(2)(ii) of this AD
to determine if certain fasteners are installed,
and, before further flight, do all applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2473, Revision 2, dated August 28,
2009; except where Boeing Alert Service
Bulletin 747–53A2473, Revision 2, dated
August 28, 2009, specifies to contact Boeing
for repair or rework data, the data must be
approved in accordance with the procedures
specified in paragraph (x) of this AD and the
repair or rework must be done before further
flight.
(i) For airplanes modified in accordance
with Boeing Service Bulletin 747–53–2473,
dated March 24, 2005: Inspect the upper
forward inner chord, frame support fitting,
and splice fitting.
(ii) For airplanes modified in accordance
with Boeing Service Bulletin 747–53–2473,
Revision 1, dated February 20, 2007: Inspect
the frame web and upper shear deck aft side;
and the upper forward inner chord, frame
support fitting, and splice fitting.
Post-Modification Inspection and Repair
(r) For airplanes on which the terminating
modification has been done in accordance
with paragraph (m) or (q) of this AD: Perform
post-modification inspections of the BS 2598
bulkhead for cracking, in accordance with
Parts 1, 2, and 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
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15:10 Feb 23, 2010
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747–53A2473, Revision 2, dated August 28,
2009. Do the inspections at the applicable
times specified in Tables 6 through 9 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2473, Revision 2,
dated August 28, 2009; except where the
service bulletin specifies a compliance time
after the date of the service bulletin, this AD
requires compliance within the specified
compliance time after the effective date of
this AD. If any cracking is found during any
inspection required by this paragraph, before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (x) of this AD. Repeat
the inspections thereafter at the applicable
times specified in Tables 6 through 9 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2473, Revision 2,
dated August 28, 2009. Accomplishing the
applicable inspections required by this
paragraph terminates the requirements of
paragraph (n) of this AD.
Open-Hole HFEC Inspection(s) and
Terminating Repair
(s) For airplanes on which the terminating
modification required by paragraph (m) or (q)
of this AD has not been done: Do an initial
open-hole HFEC inspection to detect cracks
in the bulkhead splice fitting, frame support
fitting, and forward and aft inner chords on
the left and right sides of the BS 2598
bulkhead, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2427, Revision 5,
dated October 1, 2009. Do the initial
inspection at the applicable time specified in
Table 1 or 3 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Service Bulletin 747–53A2427,
Revision 5, dated October 1, 2009; except
where Boeing Service Bulletin 747–53A2427,
Revision 5, dated October 1, 2009, specifies
a compliance time after the date on the
service bulletin, this AD requires compliance
within the specified compliance time after
the effective date of this AD.
(1) If no crack is detected, repeat the openhole HFEC inspection thereafter at intervals
not to exceed 1,500 flight cycles.
(2) If any crack is detected, before further
flight, repair it in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2427, Revision 5,
dated October 1, 2009; except where Boeing
Service Bulletin 747–53A2427, Revision 5,
dated October 1, 2009, specifies to contact
Boeing for appropriate action, before further
flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (x) of this AD.
Accomplishing the aft inner chord repair in
accordance with the applicable structural
repair manual (SRM) specified in the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2427, Revision 5,
dated October 1, 2009, ends the repetitive
surface and open-hole HFEC inspections
required by paragraphs (i) and (s)(1),
respectively, of this AD for that side of the
bulkhead only.
Interim Modification
(t) For Group 1 airplanes, as identified in
Boeing Service Bulletin 747–53A2427,
Revision 5, dated October 1, 2009, on which
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Fmt 4702
Sfmt 4702
the SRM repair required by paragraph (j) or
(s)(2) of this AD has not been done; and on
which the terminating modification required
by paragraph (m) or (q) of this AD has not
been done: Before the accumulation of 12,000
total flight cycles, or within 1,500 flight
cycles after the effective date of this AD,
whichever occurs later, install the interim
modification for the aft inner chords, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2427, Revision 5, dated October 1, 2009.
Accomplishing the interim modification ends
the repetitive surface and open-hole HFEC
inspections required by paragraphs (i) and
(s)(1), respectively, of this AD.
Post-Interim Modification/Repair Repetitive
Surface and Open-Hole HFEC Inspections
(u) For airplanes on which the interim
modification required by paragraph (t) of this
AD has been done or the SRM repair required
by paragraph (j) or (s)(2) of this AD has been
done; and on which the terminating
modification required by paragraph (m) or (q)
of this AD has not been done: At the
applicable times specified in Table 1, 2, or
3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2427, Revision 5,
dated October 1, 2009, do a surface HFEC
inspection to detect cracks on the forward
side (unmodified area) of the bulkhead, and
open-hole and surface HFEC inspections to
detect cracks in the modified or repaired
area, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2427, Revision 5,
dated October 1, 2009. Repeat the open-hole
and surface HFEC inspections thereafter at
intervals not to exceed 1,500 flight cycles,
until the modification required by paragraph
(q) of this AD is done, as applicable; except
that for airplanes on which the repair of any
cracked aft inner chord has been done on
only one side of the bulkhead in accordance
with the applicable SRM as required by
paragraph (j) or (s)(2) of this AD, the
repetitive surface and open-hole HFEC
inspections required by paragraphs (i) and
(s)(1), respectively, of this AD must continue
to be done for the other side of the bulkhead.
Repair of Any Cracked Inner Chord, Splice
Fitting, or Frame Support Fitting
(v) If any crack is detected during any
surface or open-hole HFEC inspection
required by paragraph (u) of this AD, before
further flight, repair any cracked inner chord,
splice fitting, or frame support fitting, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2427, Revision 5, dated October 1, 2009;
except where Boeing Service Bulletin 747–
53A2427, Revision 5, dated October 1, 2009,
specifies to contact Boeing for appropriate
action, before further flight, repair the crack
using a method approved in accordance with
the procedures specified in paragraph (x) of
this AD.
Actions Accomplished According to Previous
Issue of Service Bulletin
(w) Inspections, interim modification, and
repairs accomplished before the effective
date of this AD in accordance with Boeing
Alert Service Bulletin 747–53A2427,
Revision 4, dated March 6, 2008, are
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considered acceptable for compliance with
the corresponding action specified
paragraphs (i), (j), (s), (t), (u), and (v) of this
AD.
Alternative Methods of Compliance (AMOCs)
(x)(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. Send information to ATTN: Ivan
Li, Aerospace Engineer, Airframe Branch,
ANM–120S, FAA, Seattle ACO, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6437; fax (425)
917–6590. Or, e-mail information to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that 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) AMOCs approved previously in
accordance with AD 2006–05–06 are
approved as AMOCs for the corresponding
provisions of this AD.
Issued in Renton, Washington, on February
11, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–3542 Filed 2–23–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2010–0054; Airspace
Docket No. 10–ASO–11]
cprice-sewell on DSK2BSOYB1PROD with PROPOSALS
Establishment of Class D Airspace,
Modification of Class E Airspace;
Columbus, GA
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: This action proposes to
establish Class D airspace and modify
existing Class E airspace at Columbus
Metropolitan Airport, Columbus, GA. A
decrease in air traffic volume at the
airport has made it necessary to
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15:10 Feb 23, 2010
Jkt 220001
downgrade controlled airspace for the
safety and management of Instrument
Flight Rules (IFR) and Visual Flight
Rules (VFR) operations.
DATES: Comments must be received on
or before April 12, 2010.
ADDRESSES: Send comments on this
proposal to: U.S. Department of
Transportation, Docket Operations,
West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590–0001;
Telephone: 1–800–647–5527; Fax: 202–
493–2251. You must identify the Docket
Number FAA–2010–0054; Airspace
Docket No. 10–ASO–11, at the
beginning of your comments. You may
also submit and review received
comments through the Internet at
https://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Melinda Giddens, Airspace Specialist,
Operations Support Group, Eastern
Service Center, Air Traffic Organization,
Federal Aviation Administration, P.O.
Box 20636, Atlanta, Georgia 30320;
telephone (404) 305–5610.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to
comment on this rule by submitting
such written data, views, or arguments,
as they may desire. Comments that
provide the factual basis supporting the
views and suggestions presented are
particularly helpful in developing
reasoned regulatory decisions on the
proposal. Comments are specifically
invited on the overall regulatory,
aeronautical, economic, environmental,
and energy-related aspects of the
proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA
2010–0054; Airspace Docket No. 10–
ASO–11) and be submitted in triplicate
to the Docket Management System (see
ADDRESSES section for address and
phone number). You may also submit
comments through the Internet at
https://www.regulations.gov.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2010–0054; Airspace
Docket No. 10–ASO–11.’’ The postcard
will be date/time stamped and returned
to the commenter.
All communications received before
the specified closing date for comments
will be considered before taking action
on the proposed rule. The proposal
contained in this notice may be changed
in light of the comments received. A
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8285
report summarizing each substantive
public contact with FAA personnel
concerned with this rulemaking will be
filed in the docket.
Availability of NPRMs
An electronic copy of this document
may be downloaded from and
comments submitted through https://
www.regulations.gov. Recently
published rulemaking documents can
also be accessed through the FAA’s Web
page at https://www.faa.gov/
airports_airtraffic/air_traffic/
publications/airspace_amendments/.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office (see the
ADDRESSES section for address and
phone number) between 9 a.m. and 5
p.m., Monday through Friday, except
Federal Holidays. An informal docket
may also be examined during normal
business hours at the office of the
Eastern Service Center, Federal Aviation
Administration, Room 210, 1701
Columbia Avenue, College Park, Georgia
30337.
Persons interested in being placed on
a mailing list for future NPRMs should
contact the FAA’s Office of Rulemaking,
(202) 267–9677, to request a copy of
Advisory Circular No. 11–2A, Notice of
Proposed Rulemaking Distribution
System, which describes the application
procedure.
The Proposal
The FAA is considering an
amendment to Title 14, Code of Federal
Regulations (14 CFR) part 71 to establish
Class D airspace and modify existing
Class E airspace at Columbus, GA. Due
to a decrease in air traffic volume at
Columbus Metropolitan Airport a less
restrictive Class D airspace would be
established with specific dates and
times established in advance by a Notice
to Airmen. The existing Class E surface
area would be modified to be coincident
with the newly established Class D
airspace. The existing Class E airspace
extending upward from 700 feet above
the surface would be modified for the
safety and management of IFR
operations. Lawson Army Airfield,
Columbus, GA, would be removed from
the Class E2 and E5 airspace
description, and would be reestablished under separate rulemaking.
Class D airspace designations, Class
E2 surface airspace designations and
Class E5 designations are published in
Paragraphs 5000, 6002 and 6005,
respectively, of FAA Order 7400.9T,
signed August 27, 2009, and effective
September 15, 2009, which is
incorporated by reference in 14 CFR
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]]>Agencies
[Federal Register Volume 75, Number 36 (Wednesday, February 24, 2010)]
[Proposed Rules]
[Pages 8279-8285]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-3542]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0981; Directorate Identifier 2008-NM-073-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: The FAA is revising an earlier NPRM for an airworthiness
directive (AD) that applies to certain Model 747 airplanes. The
original NPRM would have superseded an existing AD that currently
requires repetitive inspections of the body station (BS) 2598 bulkhead,
and corrective actions if necessary. The existing AD also currently
requires a terminating modification for the repetitive inspections and
a post-modification inspection of the modified area. The original NPRM
proposed to continue to require those actions using revised service
information. For certain airplanes, the original NPRM proposed to
require new repetitive inspections, an interim modification, and post-
interim modification inspections. For certain airplanes, the original
NPRM also proposed to require replacing any previously repaired aft
inner chord and reinstalling the terminating modification. The original
NPRM resulted from reports of cracked aft inner chords on airplanes
after certain requirements of the existing AD were done. This new
action revises the original NPRM for airplanes that are converted to
the Model 747-400 large cargo freighter (LCF) configuration by reducing
the threshold and repeat intervals of certain post-modification
inspections. This new action also revises the original NPRM for all
airplanes by proposing that certain inspections of the upper aft outer
chords and diagonal brace attachment fittings, flanges, and rods
continue after the terminating modification. We are proposing this
supplemental NPRM to prevent fatigue cracking of the BS 2598 bulkhead
structure, which could result in inability of the structure to carry
horizontal stabilizer flight loads, and loss of controllability of the
airplane.
DATES: We must receive comments on this supplemental NPRM by March 22,
2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221 or
425-227-1152.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0981;
Directorate Identifier 2008-NM-073-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We proposed to amend part 39 of the Federal Aviation Regulations
(14 CFR part 39) with a notice of proposed rulemaking (NPRM) for an AD
(the ``original NPRM'') to supersede AD 2006-05-06, amendment 39-14503
(71 FR 12125, March 9, 2006). The original NPRM applied to certain
Model 747 airplanes. The original NPRM was published in the Federal
Register on September 23, 2008 (73 FR 54751). The original NPRM
proposed to require repetitive inspections of the body station (BS)
2598 bulkhead, and corrective actions if necessary; and a terminating
modification for the repetitive inspections and a post-modification
inspection of the modified area. The original NPRM proposed to require
those actions using revised service information. For certain airplanes,
the original NPRM proposed to require new repetitive inspections, an
interim modification, and post-interim modification inspections. For
certain airplanes, the original NPRM also proposed to require replacing
any previously repaired aft inner chord and reinstalling the
terminating modification.
Actions Since Original NPRM was Issued
Since we issued the original NPRM, Boeing informed us that the
compliance times of certain post-modification inspections need to be
revised for Model 747-400 series airplanes that have been modified to
operate in a freighter configuration. These airplanes are referred to
as large cargo freighters, or LCF. Boeing states that higher operating
[[Page 8280]]
stresses for the subject structure on the Model 747-400 LCF airplanes
mean that these airplanes need a lower inspection threshold and shorter
repeat intervals than those specified in the original NPRM. We agree,
and we have revised paragraphs (m), (q), and (r) of the original NPRM
to reduce the threshold and repetitive intervals.
In addition, Boeing informed us that for all airplanes certain
inspections of the upper aft outer chords and diagonal brace attachment
fittings, flanges, and rods need to be continued after the terminating
modification is accomplished. Adding the reinforcing modification and
replacing the aft inner chord as specified in the NPRM does not alter
the upper aft outer chord and diagonal brace attachment fittings,
flanges, and rods. Therefore, we have revised paragraph (q) of the
original NPRM to specify that certain inspections must continue after
the terminating modification.
Comments
We have considered the following comments on the original NPRM.
Request To Revise Costs of Compliance
Northwest Airlines requests that we revise the ``Costs of
Compliance'' section of the original NPRM to include Boeing's current
cost of the modification kit. Northwest Airlines states that the
current cost is $52,218 rather than the $33,716 quoted in the original
NPRM.
We agree that the cost of the modification kit has changed. We have
revised the ``Costs of Compliance'' section of this supplemental NPRM
to include the new cost of the kit.
Request To Delay the AD Pending Revised Service Information
All Nippon Airways and Japan Airlines request that we delay issuing
the AD until Boeing revises Alert Service Bulletin 747-53A2427 to
Revision 5 (we referred to Boeing Alert Service Bulletin 747-53A2427,
Revision 4, dated March 6, 2008, in the original NPRM). All Nippon
Airways explains that it has discussed several discrepancies in
Revision 4 with Boeing, and that Boeing clarified those discrepancies
in an information notice (IN). All Nippon Airways states that, since
INs are not approved by the FAA, it will be a burden to operators to
request alternative methods of compliance (AMOCs) once the proposed
rule is mandated. As an alternative, All Nippon Airways proposes that
we include the additional information from the IN in the final rule.
In addition, Boeing has informed us that there is a discrepancy in
the modification drawing specified in Boeing Alert Service Bulletin
747-53A2427, Revision 4, dated March 6, 2008. The drawing does not
include a step to ``zero-time'' certain existing fastener holes in the
affected areas. The zero-timing is intended to remove any undetectable
cracks in the affected fastener holes.
We agree that we should refer to the most recent service
information possible. We have reviewed Boeing Service Bulletin 747-
53A2427, Revision 5, dated October 1, 2009. The revised service
information includes the information in the IN referred to by the
commenter (the IN clarifies fastener codes and repair instructions) and
does not require any additional work on airplanes on which the
inspections, interim modification, and repair specified in earlier
revisions of the service bulletin were done. Therefore, we have revised
paragraphs (i), (j), (o), (s), (t), (u), and (v) of this supplemental
NPRM to refer to Boeing Service Bulletin 747-53A2427, Revision 5, dated
October 1, 2009. We have also added new paragraph (w) to the
supplemental NPRM to give credit for doing certain actions in
accordance with Boeing Alert Service Bulletin 747-53A2427, Revision 4,
dated March 6, 2008.
We have also reviewed Boeing Service Bulletin 747-53-2473, Revision
1, dated February 20, 2007; and Boeing Alert Service Bulletin 747-
53A2473, Revision 2, dated August 28, 2009. We referred to Boeing
Service Bulletin 747-53-2473, dated March 24, 2005, as the appropriate
source of service information for accomplishing the required actions
specified in paragraph (m) of the NPRM.
Boeing Service Bulletin 747-53-2473, Revision 1, dated February 20,
2007, retains and clarifies the same procedures as in Boeing Service
Bulletin 747-53-2473, dated March 24, 2005, and adds procedures to
replace repaired aft inner chords on certain airplanes on which the
actions specified in Boeing Service Bulletin 747-53-2473, dated March
24, 2005, were done.
Boeing Alert Service Bulletin 747-53A2473, Revision 2, dated August
28, 2009, adds procedures to inspect to determine if certain fasteners
were installed, and to do related investigative and corrective actions
if necessary, for airplanes on which the support frame modification
specified in Boeing Service Bulletin 747-53-2473, dated March 24, 2005;
or Revision 1, dated February 20, 2007; was done. The related
investigative actions include an open-hole high frequency eddy current
(HFEC) inspection of the fastener holes of a certain type of fastener
for cracks, and a review of maintenance records to verify that an open-
hole HFEC inspection was performed at certain other fastener holes and
the holes were zero-timed. For airplanes on which the holes were not
zero-timed, the service bulletin specifies an HFEC inspection of the
holes for cracks, and corrective actions if necessary. Boeing Alert
Service Bulletin 747-53A2473, Revision 2, dated August 28, 2009, also
adds procedures to do post-modification inspections.
We have revised paragraph (m) of this supplemental NPRM to refer to
Boeing Service Bulletin 747-53-2473, Revision 1, dated February 20,
2007; and Boeing Alert Service Bulletin 747-53A2473, Revision 2, dated
August 28, 2009. We have revised paragraph (q) of this supplemental
NPRM to refer to Boeing Alert Service Bulletin 747-53A2473, Revision 2,
dated August 28, 2009.
We have also revised paragraphs (n) and (r) of this supplemental
NPRM to refer to Boeing Alert Service Bulletin 747-53A2473, Revision 2,
dated August 28, 2009, for the post-modification inspections.
Explanation of Change to Paragraph (r) of This Supplemental NPRM
Boeing Alert Service Bulletin 747-53A2473, Revision 2, dated August
28, 2009, also adds procedures for post-modification inspections. In
paragraph (r) of the NPRM, we specified doing a post-modification
inspection for cracking and repair of any crack, in accordance with a
method approved by the FAA. Because Boeing Service Bulletin 747-
53A2473, Revision 2, dated August 28, 2009, specifies doing support
frame post-modification inspections, we have revised paragraph (r) of
this supplemental NPRM to refer to that service bulletin. The support
frame post-modification inspections consist of the following
inspections specified in Parts 1, 2, and 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2473, Revision 2,
dated August 28, 2009.
The ``Part 1--Support Frame Inspections'' include the following
inspections:
A detailed inspection for cracking of the support frame
and access cut-out forward and aft sides at station 2598.
A surface HFEC inspection for cracking of the lower floor
support chord at station 2598.
A low frequency eddy current (LFEC) inspection for
cracking of the support frame outer chord at station 2598.
A surface and open-hole HFEC inspection for cracking of
the support
[[Page 8281]]
frame outer chord and fitting at station 2598.
An ultrasonic or surface HFEC inspection for cracking of
the support frame outer chord at station 2598.
The ``Part 2--Hinge Support Inspection'' is an open-hole HFEC
inspection for cracking in the back-up fittings, frame support fitting
and hinge fitting at station 2598.
The ``Part 3--Support Frame Inspections'' include the following
inspections:
Detailed inspections for cracking of the frame web around
the periphery of the aft inner chord and the entire modified support
frame.
Surface HFEC inspections for cracking in the upper forward
inner chord, aft inner chord, upper splice fitting, lower forward inner
chord, and frame support fitting, lower splice fitting, hinge frame
support fitting.
An LFEC or open-hole HFEC for cracking in the upper aft
inner chord.
Ultrasonic inspections for cracking in the upper and lower
forward inner chord and frame support fitting.
A surface HFEC inspection for cracking of the frame web.
An LFEC for cracking in the aft outer chord.
If any cracking is found, the service bulletin specifies the corrective
action as contacting Boeing for repair data and doing the repair.
Boeing Alert Service Bulletin 747-53A2473, Revision 2, dated August
28, 2009, specifies that the initial compliance times for doing support
frame post-modification inspections ranges between within 1,500 flight
cycles after doing the modification to within 20,000 flight cycles
after doing the modification, depending on the inspection and airplane
configuration. The service bulletin specifies that the repetitive
interval for the support frame post-modification inspections ranges
between 1,000 flight cycles and 6,000 flight cycles, depending on the
inspection.
Explanation of New Compliance Time for Certain Airplanes in Paragraph
(m) of This Supplemental NPRM
For airplanes that are modified as specified in paragraph (m) of
the supplemental NPRM and are converted to the Model 747-400 Large
Cargo Freighter (LCF) configuration, the repetitive inspection
specified in paragraph (k)(2) of this AD must be done thereafter at
intervals not to exceed 1,800 flight cycles. We have revised paragraph
(m) of this AD accordingly.
Clarification of Compliance Time
We have revised paragraph (q)(2) of this supplemental NPRM to
specify that the applicable related investigative and corrective
actions must be done before further flight, as specified in Boeing
Alert Service Bulletin 747-53A2473, Revision 2, dated August 28, 2009.
Explanation of Change Made to Paragraph (x)(3) of This Supplemental
NPRM
Boeing Commercial Airplanes has received an Organization
Designation Authorization (ODA), which replaces their previous
designation as a Delegation Option Authorization (DOA) holder. We have
revised paragraph (x)(3) of this AD to delegate the authority to
approve an alternative method of compliance for any repair required by
this AD to the Boeing Commercial Airplanes ODA.
Explanation of Added/Removed Paragraphs in the Supplemental NPRM
We have added a new paragraph (d) to this supplemental NPRM to
provide the Air Transport Association (ATA) of America subject code for
this proposed AD. This code is added to make this supplemental NPRM
parallel with other new AD actions. We have re-identified subsequent
paragraphs accordingly.
Paragraph (n) of the original NPRM indicates that, after the
effective date of the AD, Boeing Alert Service Bulletin 747-53A2427,
Revision 4, dated March 6, 2008, must be used to accomplish the
requirements of paragraphs (h) and (i) of the original NPRM (i.e.,
paragraphs (i) and (j) of this supplemental NPRM). We have removed
paragraph (n) of the original NPRM, and have referred to Boeing Service
Bulletin 747-53A2427, Revision 5, dated October 1, 2009, in paragraphs
(i) and (j) of this supplemental NPRM.
Explanation of Additional Change to ``Costs of Compliance'' Paragraph
We have revised the ``Costs of Compliance'' section to clarify
which costs are retained from AD 2006-05-06 and which costs are new in
this supplemental NPRM.
Explanation of Changes Made to the Manufacturer Name
We have revised this supplemental NPRM to identify the legal name
of the manufacturer as published in the most recent type certificate
data sheet for the affected airplane models.
FAA's Determination and Proposed Requirements of the Supplemental NPRM
We are proposing this supplemental NPRM because we evaluated all
pertinent information and determined an unsafe condition exists and is
likely to exist or develop on other products of the same type design.
Certain changes described above expand the scope of the original NPRM.
As a result, we have determined that it is necessary to reopen the
comment period to provide additional opportunity for the public to
comment on this supplemental NPRM.
Costs of Compliance
There are about 998 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD. The average labor rate
is $80 per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Work U.S.-
Action hours Parts Cost per airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
Surface HFEC inspections (required 2 None $160, per inspection 162 $25,920, per
by AD 2006[dash]05[dash]06) and cycle. inspection cycle.
open-hole HFEC inspections (new
proposed action).
Detailed inspections (required by 2 None $160, per inspection 162 $25,920, per
AD 2006[dash]05[dash]06). cycle. inspection cycle.
Terminating modification 126 $52,218 $62,298............. 162 $10,092,276.
(partially required by AD
2006[dash]05[dash]06; additional
modification actions in this new
proposed action).
[[Page 8282]]
Interim modification (new proposed 4 4,000 $4,320.............. 162 $699,840.
action).
Replacement of previously repaired 2 None $160................ 162 $25,920.
aft inner chords (new proposed
action).
Support Frame upper Corner 8 None $640................ 162 $103,680.
Fastener Inspection (new proposed
action).
Post-modification inspection (new 4 None $320................ 162 $51,840.
proposed action).
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this supplemental NPRM 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14503 (71 FR 12125, March 9, 2006) and adding the
following new airworthiness directive (AD):
The Boeing Company: Docket No. FAA-2008-0981; Directorate Identifier
2008-NM-073-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 22,
2010.
Affected ADs
(b) This AD supersedes AD 2006-05-06, Amendment 39-14503.
Applicability
(c) This AD applies to The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated
in any category, line numbers 1 though 1307 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reports of cracked aft inner chords on
airplanes after certain requirements of the existing AD were done.
We are issuing this AD to prevent fatigue cracking of the body
station (BS) 2598 bulkhead structure, which could result in
inability of the structure to carry horizontal stabilizer flight
loads, and loss of controllability of the airplane.
Compliance
(f) 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 2006-05-06
Repetitive High Frequency Eddy Current (HFEC) Inspections of the
Bulkhead Frame Supports
(g) Before the accumulation of 10,000 total flight cycles, or
within 1,000 flight cycles after August 16, 2001 (the effective date
of AD 2001-14-07, amendment 39-12318, which was superseded by AD
2006-05-06), whichever occurs later: Do an open-hole HFEC inspection
to find cracking of the bulkhead frame support under the hinge
support fittings of the horizontal stabilizer on the left and right
sides at BS 2598, in accordance with Figure 2 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2449, Revision 1,
dated May 24, 2001; or Revision 2, dated March 14, 2002. Repeat the
inspection after that at intervals not to exceed 3,000 flight
cycles. Inspections accomplished before August 16, 2001, per Boeing
Alert Service Bulletin 747-53A2449, dated June 8, 2000, are
considered acceptable for compliance with the applicable inspection
specified in this paragraph.
Repair of Any Cracked Bulkhead Frame Support
(h) If any cracking is found during any inspection required by
paragraph (g) of this AD, before further flight, repair using a
method approved in accordance with the procedures specified in
paragraph (x) of this AD.
[[Page 8283]]
Repetitive Inspections of Inner Chords, Frame Support Fitting, and
Splice Fitting
(i) Do a surface HFEC inspection of the forward and aft inner
chords, the frame support, and the splice fitting of the forward
inner chord of the upper corners of the station 2598 bulkhead to
find cracking, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2427, Revision 2, dated October
5, 2000; Revision 3, dated September 27, 2001; or Boeing Service
Bulletin 747-53A2427, Revision 5, dated October 1, 2009; at the
latest of the times specified in paragraphs (i)(1) and (i)(2) of
this AD, as applicable. Repeat the inspection after that at
intervals not to exceed 1,500 flight cycles. After the effective
date of this AD, Boeing Service Bulletin 747-53A2427, Revision 5,
dated October 1, 2009, must be used.
(1) For airplanes having line numbers 1 through 1241 inclusive:
(i) Before the accumulation of 6,000 total flight cycles.
(ii) Within 500 flight cycles after August 28, 2001 (the
effective date of AD 2001-15-03, amendment 39-12337, which was
superseded by AD 2006-05-06).
(iii) For airplanes inspected before August 28, 2001, in
accordance with Boeing Alert Service Bulletin 747-53A2427, dated
December 17, 1998 (including inspections of the splice fitting); or
Revision 1, dated October 28, 1999: Within 1,500 flight cycles after
accomplishment of the last inspection done in accordance with the
original service bulletin or Revision 1, as applicable.
(2) For airplanes having line numbers 1242 through 1307
inclusive:
(i) Before the accumulation of 16,000 total flight cycles.
(ii) Within 500 flight cycles after August 28, 2001.
(iii) For airplanes inspected before August 28, 2001, in
accordance with Boeing Alert Service Bulletin 747-53A2427, dated
December 17, 1998 (including inspections of the splice fitting), or
Revision 1, dated October 28, 1999: Within 1,500 flight cycles after
accomplishment of the last inspection done in accordance with Boeing
Alert Service Bulletin 747-53A2427, dated December 17, 1998; or
Revision 1, dated October 28, 1999, as applicable.
Repair of Any Cracked Inner Chord, Frame Support, or Splice Fitting
(j) If any cracking is found during the inspections required by
paragraph (i) of this AD, before further flight, repair in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2427, Revision 2, dated October 5, 2000;
Revision 3, dated September 27, 2001; or Boeing Service Bulletin
747-53A2427, Revision 5, dated October 1, 2009. After the effective
date of this AD, Boeing Service Bulletin 747-53A2427, Revision 5,
dated October 1, 2009, must be used. Where Boeing Alert Service
Bulletin 747-53A2427, Revision 2, dated October 5, 2000; Revision 3,
dated September 27, 2001; or Boeing Service Bulletin 747-53A2427,
Revision 5, dated October 1, 2009; specifies that the manufacturer
may be contacted for disposition of certain repair conditions,
before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (x) of this AD.
Repetitive Detailed Inspections of BS 2598 Bulkhead
(k) Before the accumulation of 10,000 total flight cycles, or
within 1,000 flight cycles after October 27, 2003 (the effective
date of AD 2003-19-08, amendment 39-13311, which was superseded by
AD 2006-05-06), whichever is later: Do a detailed inspection of the
BS 2598 bulkhead for discrepancies (cracking, elongated fastener
holes) of the areas specified in paragraphs (k)(1) and (k)(2) of
this AD, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2467, dated July 26, 2001; or
Revision 1, dated April 28, 2005. Repeat the inspections after that
at intervals not to exceed 3,000 flight cycles, except as required
by paragraph (m) of this AD. Doing the modification specified in
paragraph (m) or (q) of this AD terminates the inspection of the
area specified in paragraph (k)(1) of this AD.
(1) The lower aft inner chords.
(2) The upper aft outer chords, and the diagonal brace
attachment fittings, flanges, and rods.
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
mirrors magnifying lenses, etc. may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repair of Any Cracked BS 2598 Bulkhead
(l) If any discrepancy is found during any inspection required
by paragraph (k) of this AD: Before further flight, repair in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2467, dated July 26, 2001; or Revision 1,
dated April 28, 2005. If the service bulletin specifies to contact
Boeing for appropriate action: Before further flight, repair using a
method approved in accordance with the procedures specified in
paragraph (x) of this AD.
Terminating Modification With New Compliance Time for Certain
Airplanes for the Inspection Specified in Paragraph (k)(2) of This
AD
(m) Except as provided by paragraph (q) of this AD: Before the
accumulation of 20,000 total flight cycles, or within 48 months
after April 13, 2006 (the effective date of AD 2006-05-06),
whichever occurs later, modify the bulkhead by doing all applicable
actions including surface and open-hole HFEC inspections for
cracking of the upper forward inner chords, aft inner chords, upper
splice fittings, and frame support fittings, as specified in the
Accomplishment Instructions of Boeing Service Bulletin 747-53-2473,
dated March 24, 2005; Revision 1, dated February 20, 2007; or Boeing
Alert Service Bulletin 747-53A2473, Revision 2, dated August 28,
2009. Repair any cracks before further flight, in accordance with
Boeing Service Bulletin 747-53-2473, dated March 24, 2005; Revision
1, dated February 20, 2007; or Boeing Alert Service Bulletin 747-
53A2473, Revision 2, dated August 28, 2009. Where Boeing Service
Bulletin 747-53-2473, dated March 24, 2005; Revision 1, dated
February 20, 2007; or Boeing Alert Service Bulletin 747-53A2473,
Revision 2, dated August 28, 2009 specifies that the manufacturer
may be contacted for disposition of certain repair conditions:
Before further flight, repair the cracks using a method approved in
accordance with the procedures specified in paragraph (x) of this
AD. Accomplishment of the modification terminates the requirements
of paragraphs (g), (i), and (k)(1) of this AD. After the effective
date of this AD, Boeing Alert Service Bulletin 747-53A2473, Revision
2, dated August 28, 2009 must be used for the actions specified in
this paragraph. For airplanes that are converted to the Model 747-
400 Large Cargo Freighter (LCF) configuration, repeat the inspection
specified in paragraph (k)(2) of this AD thereafter at intervals not
to exceed 1,800 flight cycles.
Post-Modification Inspection and Repair
(n) Except as provided by paragraphs (q) and (r) of this AD:
Within 20,000 flight cycles after doing the modification required by
paragraph (m) of this AD, inspect the BS 2598 bulkhead for cracks,
and repair any cracks before further flight, in accordance with a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO).
New Requirements of This AD
Terminating Repair for Repetitive Surface HFEC Inspections
(o) As of the effective date of this AD, accomplishing the aft
inner chord repair required by paragraph (j) of this AD in
accordance with the applicable structural repair manual (SRM)
specified in the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2427, Revision 5, dated October 1, 2009, ends the
repetitive surface HFEC inspections required by paragraph (i) of
this AD for that side of the bulkhead only.
Replacement of Previously Repaired Aft Inner Chord and
Reinstallation of Terminating Modification
(p) For airplanes on which the terminating modification required
by paragraph (m) of this AD has been done in accordance with Boeing
Service Bulletin 747-53-2473, dated March 24, 2005: Within 1,500
flight cycles after doing the modification, or within 1,000 flight
cycles after the effective date of this AD, whichever occurs later,
do a one-time general visual inspection for repairs installed
previously on the left and right side aft inner chords. For
airplanes with previously installed repairs, before further flight,
do rework (i.e., replace any previously repaired aft inner chord
with a new aft inner chord and reinstall the terminating
modification), using a method approved in accordance with the
procedures specified in paragraph (x) of this AD.
[[Page 8284]]
Revised Terminating Modification
(q) Doing the applicable modification required by paragraph
(q)(1) or (q)(2) of this AD at the applicable time terminates the
requirements of paragraph (m) of this AD and the repetitive
inspections required by paragraphs (g), (i), and (k)(1) of this AD.
For airplanes that are converted to the Model 747-400 LCF
configuration, the inspection specified in paragraph (k)(2) of this
AD must be repeated thereafter at intervals not to exceed 1,800
flight cycles.
(1) For airplanes on which the terminating modification required
by paragraph (m) of this AD has not been done as of the effective
date of this AD: Before the accumulation of 20,000 total flight
cycles, or within 18 months after the effective date of this AD,
whichever occurs later, modify the bulkhead, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2473, Revision 2, dated August 28, 2009; except that where Boeing
Alert Service Bulletin 747-53A2473, Revision 2, dated August 28,
2009, specifies to contact Boeing for modification data, the
modification data must be approved in accordance with the procedures
specified in paragraph (x) of this AD and the modification must be
done within the times specified in this paragraph.
(2) For airplanes on which the terminating modification required
by paragraph (m) of this AD has been done in accordance with Boeing
Service Bulletin 747-53-2473, dated March 24, 2005; or Revision 1,
dated February 20, 2007; as of the effective date of this AD: Within
1,000 flight cycles after the effective date of this AD, or within
1,500 flight cycles after doing the modification, whichever occurs
later, do a general visual inspection of the applicable areas
specified in paragraphs (q)(2)(i) and (q)(2)(ii) of this AD to
determine if certain fasteners are installed, and, before further
flight, do all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2473, Revision 2, dated August
28, 2009; except where Boeing Alert Service Bulletin 747-53A2473,
Revision 2, dated August 28, 2009, specifies to contact Boeing for
repair or rework data, the data must be approved in accordance with
the procedures specified in paragraph (x) of this AD and the repair
or rework must be done before further flight.
(i) For airplanes modified in accordance with Boeing Service
Bulletin 747-53-2473, dated March 24, 2005: Inspect the upper
forward inner chord, frame support fitting, and splice fitting.
(ii) For airplanes modified in accordance with Boeing Service
Bulletin 747-53-2473, Revision 1, dated February 20, 2007: Inspect
the frame web and upper shear deck aft side; and the upper forward
inner chord, frame support fitting, and splice fitting.
Post-Modification Inspection and Repair
(r) For airplanes on which the terminating modification has been
done in accordance with paragraph (m) or (q) of this AD: Perform
post-modification inspections of the BS 2598 bulkhead for cracking,
in accordance with Parts 1, 2, and 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2473, Revision
2, dated August 28, 2009. Do the inspections at the applicable times
specified in Tables 6 through 9 of paragraph 1.E., ``Compliance,''
of Boeing Service Bulletin 747-53A2473, Revision 2, dated August 28,
2009; except where the service bulletin specifies a compliance time
after the date of the service bulletin, this AD requires compliance
within the specified compliance time after the effective date of
this AD. If any cracking is found during any inspection required by
this paragraph, before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(x) of this AD. Repeat the inspections thereafter at the applicable
times specified in Tables 6 through 9 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 2,
dated August 28, 2009. Accomplishing the applicable inspections
required by this paragraph terminates the requirements of paragraph
(n) of this AD.
Open-Hole HFEC Inspection(s) and Terminating Repair
(s) For airplanes on which the terminating modification required
by paragraph (m) or (q) of this AD has not been done: Do an initial
open-hole HFEC inspection to detect cracks in the bulkhead splice
fitting, frame support fitting, and forward and aft inner chords on
the left and right sides of the BS 2598 bulkhead, in accordance with
the Accomplishment Instructions of Boeing Service Bulletin 747-
53A2427, Revision 5, dated October 1, 2009. Do the initial
inspection at the applicable time specified in Table 1 or 3 of
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2427, Revision 5, dated October 1, 2009; except where Boeing
Service Bulletin 747-53A2427, Revision 5, dated October 1, 2009,
specifies a compliance time after the date on the service bulletin,
this AD requires compliance within the specified compliance time
after the effective date of this AD.
(1) If no crack is detected, repeat the open-hole HFEC
inspection thereafter at intervals not to exceed 1,500 flight
cycles.
(2) If any crack is detected, before further flight, repair it
in accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2427, Revision 5, dated October 1, 2009; except
where Boeing Service Bulletin 747-53A2427, Revision 5, dated October
1, 2009, specifies to contact Boeing for appropriate action, before
further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (x) of this
AD. Accomplishing the aft inner chord repair in accordance with the
applicable structural repair manual (SRM) specified in the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2427,
Revision 5, dated October 1, 2009, ends the repetitive surface and
open-hole HFEC inspections required by paragraphs (i) and (s)(1),
respectively, of this AD for that side of the bulkhead only.
Interim Modification
(t) For Group 1 airplanes, as identified in Boeing Service
Bulletin 747-53A2427, Revision 5, dated October 1, 2009, on which
the SRM repair required by paragraph (j) or (s)(2) of this AD has
not been done; and on which the terminating modification required by
paragraph (m) or (q) of this AD has not been done: Before the
accumulation of 12,000 total flight cycles, or within 1,500 flight
cycles after the effective date of this AD, whichever occurs later,
install the interim modification for the aft inner chords, in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2427, Revision 5, dated October 1, 2009.
Accomplishing the interim modification ends the repetitive surface
and open-hole HFEC inspections required by paragraphs (i) and
(s)(1), respectively, of this AD.
Post-Interim Modification/Repair Repetitive Surface and Open-Hole
HFEC Inspections
(u) For airplanes on which the interim modification required by
paragraph (t) of this AD has been done or the SRM repair required by
paragraph (j) or (s)(2) of this AD has been done; and on which the
terminating modification required by paragraph (m) or (q) of this AD
has not been done: At the applicable times specified in Table 1, 2,
or 3 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin
747-53A2427, Revision 5, dated October 1, 2009, do a surface HFEC
inspection to detect cracks on the forward side (unmodified area) of
the bulkhead, and open-hole and surface HFEC inspections to detect
cracks in the modified or repaired area, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2427,
Revision 5, dated October 1, 2009. Repeat the open-hole and surface
HFEC inspections thereafter at intervals not to exceed 1,500 flight
cycles, until the modification required by paragraph (q) of this AD
is done, as applicable; except that for airplanes on which the
repair of any cracked aft inner chord has been done on only one side
of the bulkhead in accordance with the applicable SRM as required by
paragraph (j) or (s)(2) of this AD, the repetitive surface and open-
hole HFEC inspections required by paragraphs (i) and (s)(1),
respectively, of this AD must continue to be done for the other side
of the bulkhead.
Repair of Any Cracked Inner Chord, Splice Fitting, or Frame Support
Fitting
(v) If any crack is detected during any surface or open-hole
HFEC inspection required by paragraph (u) of this AD, before further
flight, repair any cracked inner chord, splice fitting, or frame
support fitting, in accordance with the Accomplishment Instructions
of Boeing Service Bulletin 747-53A2427, Revision 5, dated October 1,
2009; except where Boeing Service Bulletin 747-53A2427, Revision 5,
dated October 1, 2009, specifies to contact Boeing for appropriate
action, before further flight, repair the crack using a method
approved in accordance with the procedures specified in paragraph
(x) of this AD.
Actions Accomplished According to Previous Issue of Service
Bulletin
(w) Inspections, interim modification, and repairs accomplished
before the effective date of this AD in accordance with Boeing Alert
Service Bulletin 747-53A2427, Revision 4, dated March 6, 2008, are
[[Page 8285]]
considered acceptable for compliance with the corresponding action
specified paragraphs (i), (j), (s), (t), (u), and (v) of this AD.
Alternative Methods of Compliance (AMOCs)
(x)(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. Send information to ATTN: Ivan Li, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-
6437; fax (425) 917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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 Boeing
Commercial Airplanes Organization Designation Authorization (ODA)
that 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) AMOCs approved previously in accordance with AD 2006-05-06
are approved as AMOCs for the corresponding provisions of this AD.
Issued in Renton, Washington, on February 11, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-3542 Filed 2-23-10; 8:45 am]
BILLING CODE 4910-13-P
