Airworthiness Directives; Boeing Model 747 Airplanes, 60744-60747 [05-20882]
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60744
Proposed Rules
Federal Register
Vol. 70, No. 201
Wednesday, October 19, 2005
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
FEDERAL ELECTION COMMISSION
RIN 2120–AA64
11 CFR Part 100
Airworthiness Directives; Boeing
Model 747 Airplanes
[Notice 2005–25]
AGENCY:
Electioneering Communications
AGENCY:
ACTION:
Federal Election Commission.
Notice of public hearing.
The Federal Election
Commission is announcing a public
hearing on the proposed changes to its
rule defining ‘‘electioneering
communications’’ under the Federal
Election Campaign Act of 1971, as
amended.
SUMMARY:
The hearings will be held on
Thursday, October 20, 2005 and will
begin at 9:30 a.m.
DATES:
Commission hearings are
held in the Commission’s ninth floor
meeting room, 999 E Street, NW.,
Washington, DC.
ADDRESSES:
Ms.
Mai T. Dinh, Assistant General Counsel,
999 E Street, NW., Washington, DC
20463, (202) 694–1650 or (800) 424–
9530.
FOR FURTHER INFORMATION CONTACT:
On August
24, 2005, the Commission published a
Notice of Proposed Rulemaking
(‘‘NPRM’’) proposing revisions to its
rule defining ‘‘electioneering
communications’’ under the Federal
Election Campaign Act of 1971, as
amended. In the NPRM, the
Commission stated it would hold a
hearing on the proposed rules on
October 19 and, if necessary, October
20, 2005. The Commission has
determined that one day of public
hearing will be sufficient. The hearing
will be held on Thursday, October 20,
2005.
SUPPLEMENTARY INFORMATION:
Dated: October 13, 2005.
Scott E. Thomas,
Chairman, Federal Election Commission.
[FR Doc. 05–20866 Filed 10–18–05; 8:45 am]
BILLING CODE 6715–01–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22715; Directorate
Identifier 2005–NM–108–AD]
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: The FAA proposes to
supersede three existing airworthiness
directives (ADs) that apply to certain
Boeing Model 747 airplanes. The
existing ADs currently require repetitive
inspections of the body station (BS)
2598 bulkhead, and corrective action if
necessary. This proposed AD would add
a requirement to modify the bulkhead,
including a one-time inspection and
corrective action if necessary, which
would terminate certain repetitive
inspections. This proposed AD would
also require a post-modification
inspection of the modified area. This
proposed AD results from new reports
of cracking in all three areas that require
inspection in accordance with the
existing ADs. We are proposing this AD
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 reduced controllability of the
airplane.
We must receive comments on
this proposed AD by December 5, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
DATES:
PO 00000
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• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Nicholas Kusz, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6432; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Include the
docket number ‘‘Docket No. FAA–2005–
22715; Directorate Identifier 2005–NM–
108–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
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Federal Register / Vol. 70, No. 201 / Wednesday, October 19, 2005 / Proposed Rules
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
60745
Discussion
We have issued the ADs listed in the
following table.
EXISTING ADS
AD
Amendment
Federal Register reference
Requirements
Repetitive high-frequency eddy current
(HFEC) inspections to detect cracking of
the bulkhead frame support at body station 2598 under the hinge support fittings
of the horizontal stabilizer, and repair if
necessary.
Repetitive HFEC inspections to detect
cracking of the forward and aft inner
chords and the splice fitting of the forward
inner chord of the body station 2598 bulkhead, and repair if necessary.
Repetitive detailed inspections to detect discrepancies of certain areas of the forward
and aft sides of the body station 2598
bulkhead, and repair if necessary.
2001–14–07 .................................
39–12318
66 FR 36443 (July 12, 2001) ........................
2001–15–03 .................................
39–12337
66 FR 38365 (July 24, 2001) ........................
2003–19–08 .................................
39–13311
68 FR 54990 (September 22, 2003) .............
The existing ADs apply to airplanes
having line numbers 1 through 1307
inclusive. The existing ADs were
prompted by reports of fatigue cracking
on the body station 2598 bulkhead.
We issued those ADs to detect and
correct discrepancies of the bulkhead
structure, which could result in the
inability of the structure to carry
horizontal stabilizer flight loads, and
reduced controllability of the airplane.
Actions Since Existing AD Was Issued
Since we issued those ADs, we have
received additional reports of cracking
in all three of the areas addressed in the
existing ADs. The cracking was found
on Model 747–200B, 747–200F, and
747–400 series airplanes. Also, we
received a report of cracking found in
all three areas on one airplane.
ADs 2001–15–03 and 2003–19–08
considered the requirements ‘‘interim
action’’ and indicated that the
manufacturer was developing a
modification to address the unsafe
condition. Those ADs explained that we
may consider further rulemaking if a
modification is developed, approved,
and available. The manufacturer now
has developed such a modification, and
we have determined that further
rulemaking is indeed necessary; this
proposed AD follows from that
determination.
Relevant Service Information
We have reviewed Boeing Service
Bulletin 747–53–2473, dated March 24,
2005. The service bulletin describes
procedures for modifying the bulkhead.
The modification involves:
• Inspecting specified areas using
surface high-frequency eddy current
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(HFEC) and open-hole HFEC methods to
detect cracks;
• Repairing cracks;
• Removing the bulkhead upper and
lower diagonal braces by using a special
tool between their attachment fittings to
lift and hold the horizontal stabilizer;
• Installing the following on the aft
side of the bulkhead on both sides of the
airplane: Two web doublers, new upper
and lower hinge backup fittings, and
either a new inner chord or the original
inner chord that has been inspected for
cracks and repaired if necessary; and
• Installing oversize fasteners at
specified locations where insurance cuts
have been made to remove material that
could contain an undetected crack.
AD 2003–19–08 refers to Boeing Alert
Service Bulletin 747–53A2467, dated
July 26, 2001, as the appropriate source
of service information for the required
actions. Boeing has since issued
Revision 1, dated April 28, 2005.
Revision 1 clarifies certain instructions,
but the procedures are essentially the
same as those in the original service
bulletin.
AD 2001–14–07 refers to Boeing
Service Bulletin 747–53A2449, Revision
1, dated May 24, 2001, as the
appropriate source of service
information for the required actions.
Boeing has since issued Revision 2,
dated March 14, 2002. Revision 2
clarifies certain instructions, but the
procedures are essentially the same as
those in Revision 1.
AD 2001–15–03 refers to Boeing Alert
Service Bulletin 747–53A2427, dated
December 17, 1998, and Revision 1,
dated October 28, 1999, as the
appropriate source of service
information for the required actions.
Boeing has since issued Revision 2,
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dated October 5, 2000, and Revision 3,
dated September 27, 2001. Revisions 2
and 3 clarify certain instructions, but
the procedures are essentially the same
as those in the applicable versions cited
in AD 2001–15–03.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other airplanes of the same
type design that may be registered in the
U.S. at some time in the future. For this
reason, we are proposing this AD, which
would supersede ADs 2001–14–07,
2001–15–03, and 2003–19–08. This
proposed AD would retain the
requirements of the existing ADs and
add the actions specified in the service
bulletin described previously, except as
discussed below.
Difference Between the Proposed AD
and the Service Bulletin
The service bulletin specifies
contacting the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions by
either using a method that we approve
or using data that meet the certification
basis of the airplane and that have been
approved by an Authorized
Representative for the Boeing
Commercial Airplanes Delegation
Option Authorization Organization
whom we have authorized to make
those findings.
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Federal Register / Vol. 70, No. 201 / Wednesday, October 19, 2005 / Proposed Rules
Additional Changes to Existing ADs
Boeing Commercial Airplanes has
received a Delegation Option
Authorization (DOA). We have revised
the existing AD to delegate the authority
to approve an alternative method of
compliance for any repair specified in
this proposed AD to an Authorized
Representative for the Boeing
Commercial Airplanes DOA rather than
the Designated Engineering
Representative (DER).
We have changed all references to a
‘‘detailed visual inspection’’ in the
existing ADs to ‘‘detailed inspection’’ in
this action. Note 1 in this proposed AD
defines a detailed inspection.
In the existing ADs, credit for
accomplishment of a prior revision of a
service bulletin was provided in a note;
in this proposed AD, that language has
been added to paragraph (f).
Costs of Compliance
There are about 1,147 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.
ESTIMATED COSTS
Average
hourly labor
rate
18
$65
$0
$1,170
280
$327,600
2
65
0
130
280
36,400
2
65
0
130
280
36,400
4
126
65
65
0
33,716
260
41,906
280
280
72,800
11,733,680
Inspection required by AD 2001–14–
07 (per inspection cycle) ................
HFEC inspection required by AD
2001–15–03 (per inspection cycle)
Detailed inspection required by AD
2001–15–03 (per inspection cycle)
Inspection required by AD 2003–19–
08 (per inspection cycle) ................
Proposed modification .......................
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;
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Number of
U.S.registered
airplanes
Work hours
Actions
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Parts
Cost per airplane
Fleet cost
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 proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
Boeing: Docket No. FAA–2005–22715;
Directorate Identifier 2005–NM–108–AD.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
AD Amendment
2001–14–07.
AD Amendment
2001–15–03.
AD Amendment
2003–19–08.
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–12318 (66
FR 36443, July 12, 2001), amendment
39–12337 (66 FR 38365, July 24, 2001),
and amendment 39–13311 (68 FR
54990, September 22, 2003), and adding
the following new airworthiness
directive (AD):
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Comments Due Date
(a) The FAA must receive comments on
this AD action by December 5, 2005.
Affected ADs
(b) This AD supersedes the ADs listed in
Table 1 of this AD.
TABLE 1.—SUPERSEDED ADS
AD
Amendment
Amendment 39–
12318.
Amendment 39–
12337.
Amendment 39–
13311.
Applicability
(c) This AD applies to Boeing 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 through 1307 inclusive.
Unsafe Condition
(d) This AD results from reports of cracking
in areas required to be inspected by the
superseded ADs identified in Table 1 of this
AD. 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 reduced
controllability of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
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Restatement of AD 2001–14–07
Repetitive High Frequency Eddy Current
(HFEC) Inspections
(f) 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), 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.
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.
Repair
(i) If any cracking is found during the
inspections required by paragraph (h) 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; or
Revision 3, dated September 27, 2001; except
where the alert service bulletin specifies that
the manufacturer may be contacted for
disposition of certain repair conditions,
before further flight, repair in accordance
with a method approved by the Manager,
Seattle ACO, or using a method approved in
accordance with paragraph (n)(5) of this AD.
the compliance times specified, unless the
actions have already been done.
Repair
(g) If any cracking is found during any
inspection required by paragraph (f) of this
AD, before further flight, repair in accordance
with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO),
FAA, or using a method approved in
accordance with paragraph (n)(5) of this AD.
Restatement of Certain Requirements of AD
2001–15–03
Repetitive Inspections
(h) 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 corner 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; or Revision 3, dated September 27,
2001; at the latest of the times specified in
paragraphs (h)(1) and (h)(2) of this AD, as
applicable. Repeat the inspection after that at
intervals not to exceed 1,500 flight cycles.
(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).
(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
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effective date of this AD, 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 chord, aft inner
chord, upper splice fitting, and frame support
fitting, as specified in the Accomplishment
Instructions of Boeing Service Bulletin 747–
53–2473, dated March 24, 2005. Repair any
cracks before further flight in accordance
with the service bulletin. Where the service
bulletin 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 (n) or (n)(5) of this AD.
Accomplishment of the modification
terminates the repetitive inspections required
by paragraphs (f), (h), and (j)(1) of this AD.
Inspection
Restatement of AD 2003–19–08
Repetitive Inspections
(j) 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), whichever is later: Do a
detailed inspection of the body station 2598
bulkhead for discrepancies (cracking,
elongated fastener holes) of the areas
specified in paragraphs (j)(1) and (j)(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.
(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
(k) If any discrepancy is found during any
inspection required by paragraph (j) 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 any
discrepancy is found and the service bulletin
specifies to contact Boeing for appropriate
action: Before further flight, repair in
accordance with a method approved by the
Manager, Seattle ACO, or using a method
approved in accordance with paragraph
(n)(5) of this AD.
New Requirements of This AD
(m) Within 20,000 flight cycles after the
modification required by paragraph (l) of this
AD, inspect the body station 2598 bulkhead
for cracks, and repair any cracks before
further flight, in accordance with a method
approved by the Manager, Seattle ACO.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) AMOCs approved previously according
to AD 2000–08–21, amendment 39–11707,
and AD 2001–15–03 are approved as AMOCs
for the corresponding requirements of
paragraphs (h) and (i) of this AD. (AD 2000–
08–21 was superseded by AD 2001–15–03.)
(3) AMOCs approved previously according
to AD 2001–14–07 are approved as AMOCs
for the corresponding requirements of
paragraphs (f) and (g) of this AD.
(4) AMOCs approved previously according
to AD 2003–19–08 are approved as AMOCs
for the corresponding requirements of
paragraphs (j) and (k) of this AD.
(5) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Issued in Renton, Washington, on
September 28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–20882 Filed 10–18–05; 8:45 am]
BILLING CODE 4910–13–P
Modification
(l) Before the accumulation of 20,000 total
flight cycles, or within 48 months after the
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]]>Agencies
[Federal Register Volume 70, Number 201 (Wednesday, October 19, 2005)]
[Proposed Rules]
[Pages 60744-60747]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-20882]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22715; Directorate Identifier 2005-NM-108-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede three existing airworthiness
directives (ADs) that apply to certain Boeing Model 747 airplanes. The
existing ADs currently require repetitive inspections of the body
station (BS) 2598 bulkhead, and corrective action if necessary. This
proposed AD would add a requirement to modify the bulkhead, including a
one-time inspection and corrective action if necessary, which would
terminate certain repetitive inspections. This proposed AD would also
require a post-modification inspection of the modified area. This
proposed AD results from new reports of cracking in all three areas
that require inspection in accordance with the existing ADs. We are
proposing this AD 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 reduced controllability of the
airplane.
DATES: We must receive comments on this proposed AD by December 5,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Nicholas Kusz, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6432; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Include the docket number
``Docket No. FAA-2005-22715; Directorate Identifier 2005-NM-108-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or may
visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone
[[Page 60745]]
(800) 647-5227) is located on the plaza level of the Nassif Building at
the DOT street address stated in the ADDRESSES section. Comments will
be available in the AD docket shortly after the Docket Management
System receives them.
Discussion
We have issued the ADs listed in the following table.
Existing ADs
----------------------------------------------------------------------------------------------------------------
AD Amendment Federal Register reference Requirements
----------------------------------------------------------------------------------------------------------------
2001-14-07.......................... 39-12318 66 FR 36443 (July 12, 2001). Repetitive high-frequency
eddy current (HFEC)
inspections to detect
cracking of the bulkhead
frame support at body
station 2598 under the
hinge support fittings of
the horizontal stabilizer,
and repair if necessary.
2001-15-03.......................... 39-12337 66 FR 38365 (July 24, 2001). Repetitive HFEC inspections
to detect cracking of the
forward and aft inner
chords and the splice
fitting of the forward
inner chord of the body
station 2598 bulkhead, and
repair if necessary.
2003-19-08.......................... 39-13311 68 FR 54990 (September 22, Repetitive detailed
2003). inspections to detect
discrepancies of certain
areas of the forward and
aft sides of the body
station 2598 bulkhead, and
repair if necessary.
----------------------------------------------------------------------------------------------------------------
The existing ADs apply to airplanes having line numbers 1 through
1307 inclusive. The existing ADs were prompted by reports of fatigue
cracking on the body station 2598 bulkhead.
We issued those ADs to detect and correct discrepancies of the
bulkhead structure, which could result in the inability of the
structure to carry horizontal stabilizer flight loads, and reduced
controllability of the airplane.
Actions Since Existing AD Was Issued
Since we issued those ADs, we have received additional reports of
cracking in all three of the areas addressed in the existing ADs. The
cracking was found on Model 747-200B, 747-200F, and 747-400 series
airplanes. Also, we received a report of cracking found in all three
areas on one airplane.
ADs 2001-15-03 and 2003-19-08 considered the requirements ``interim
action'' and indicated that the manufacturer was developing a
modification to address the unsafe condition. Those ADs explained that
we may consider further rulemaking if a modification is developed,
approved, and available. The manufacturer now has developed such a
modification, and we have determined that further rulemaking is indeed
necessary; this proposed AD follows from that determination.
Relevant Service Information
We have reviewed Boeing Service Bulletin 747-53-2473, dated March
24, 2005. The service bulletin describes procedures for modifying the
bulkhead. The modification involves:
Inspecting specified areas using surface high-frequency
eddy current (HFEC) and open-hole HFEC methods to detect cracks;
Repairing cracks;
Removing the bulkhead upper and lower diagonal braces by
using a special tool between their attachment fittings to lift and hold
the horizontal stabilizer;
Installing the following on the aft side of the bulkhead
on both sides of the airplane: Two web doublers, new upper and lower
hinge backup fittings, and either a new inner chord or the original
inner chord that has been inspected for cracks and repaired if
necessary; and
Installing oversize fasteners at specified locations where
insurance cuts have been made to remove material that could contain an
undetected crack.
AD 2003-19-08 refers to Boeing Alert Service Bulletin 747-53A2467,
dated July 26, 2001, as the appropriate source of service information
for the required actions. Boeing has since issued Revision 1, dated
April 28, 2005. Revision 1 clarifies certain instructions, but the
procedures are essentially the same as those in the original service
bulletin.
AD 2001-14-07 refers to Boeing Service Bulletin 747-53A2449,
Revision 1, dated May 24, 2001, as the appropriate source of service
information for the required actions. Boeing has since issued Revision
2, dated March 14, 2002. Revision 2 clarifies certain instructions, but
the procedures are essentially the same as those in Revision 1.
AD 2001-15-03 refers to Boeing Alert Service Bulletin 747-53A2427,
dated December 17, 1998, and Revision 1, dated October 28, 1999, as the
appropriate source of service information for the required actions.
Boeing has since issued Revision 2, dated October 5, 2000, and Revision
3, dated September 27, 2001. Revisions 2 and 3 clarify certain
instructions, but the procedures are essentially the same as those in
the applicable versions cited in AD 2001-15-03.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of the same type design that may be registered in the U.S. at some time
in the future. For this reason, we are proposing this AD, which would
supersede ADs 2001-14-07, 2001-15-03, and 2003-19-08. This proposed AD
would retain the requirements of the existing ADs and add the actions
specified in the service bulletin described previously, except as
discussed below.
Difference Between the Proposed AD and the Service Bulletin
The service bulletin specifies contacting the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions by either using a method that
we approve or using data that meet the certification basis of the
airplane and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
[[Page 60746]]
Additional Changes to Existing ADs
Boeing Commercial Airplanes has received a Delegation Option
Authorization (DOA). We have revised the existing AD to delegate the
authority to approve an alternative method of compliance for any repair
specified in this proposed AD to an Authorized Representative for the
Boeing Commercial Airplanes DOA rather than the Designated Engineering
Representative (DER).
We have changed all references to a ``detailed visual inspection''
in the existing ADs to ``detailed inspection'' in this action. Note 1
in this proposed AD defines a detailed inspection.
In the existing ADs, credit for accomplishment of a prior revision
of a service bulletin was provided in a note; in this proposed AD, that
language has been added to paragraph (f).
Costs of Compliance
There are about 1,147 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.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Actions Work hours hourly Parts Cost per airplane registered Fleet cost
labor rate airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection required by AD 2001-14-07 (per inspection 18 $65 $0 $1,170 280 $327,600
cycle).................................................
HFEC inspection required by AD 2001-15-03 (per 2 65 0 130 280 36,400
inspection cycle)......................................
Detailed inspection required by AD 2001-15-03 (per 2 65 0 130 280 36,400
inspection cycle)......................................
Inspection required by AD 2003-19-08 (per inspection 4 65 0 260 280 72,800
cycle).................................................
Proposed modification................................... 126 65 33,716 41,906 280 11,733,680
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 39-12318 (66 FR 36443, July 12, 2001), amendment 39-
12337 (66 FR 38365, July 24, 2001), and amendment 39-13311 (68 FR
54990, September 22, 2003), and adding the following new airworthiness
directive (AD):
Boeing: Docket No. FAA-2005-22715; Directorate Identifier 2005-NM-
108-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
5, 2005.
Affected ADs
(b) This AD supersedes the ADs listed in Table 1 of this AD.
Table 1.--Superseded ADs
------------------------------------------------------------------------
AD Amendment
------------------------------------------------------------------------
AD Amendment 2001-14-07................... Amendment 39-12318.
AD Amendment 2001-15-03................... Amendment 39-12337.
AD Amendment 2003-19-08................... Amendment 39-13311.
------------------------------------------------------------------------
Applicability
(c) This AD applies to Boeing 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 through 1307 inclusive.
Unsafe Condition
(d) This AD results from reports of cracking in areas required
to be inspected by the superseded ADs identified in Table 1 of this
AD. 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 reduced controllability of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within
[[Page 60747]]
the compliance times specified, unless the actions have already been
done.
Restatement of AD 2001-14-07
Repetitive High Frequency Eddy Current (HFEC) Inspections
(f) 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), 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
(g) If any cracking is found during any inspection required by
paragraph (f) of this AD, before further flight, repair in
accordance with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA, or using a method approved in
accordance with paragraph (n)(5) of this AD.
Restatement of Certain Requirements of AD 2001-15-03
Repetitive Inspections
(h) 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 corner 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; or Revision 3, dated September 27, 2001; at the latest of
the times specified in paragraphs (h)(1) and (h)(2) of this AD, as
applicable. Repeat the inspection after that at intervals not to
exceed 1,500 flight cycles.
(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).
(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 the
original service bulletin or Revision 1, as applicable.
Repair
(i) If any cracking is found during the inspections required by
paragraph (h) 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; or
Revision 3, dated September 27, 2001; except where the alert service
bulletin specifies that the manufacturer may be contacted for
disposition of certain repair conditions, before further flight,
repair in accordance with a method approved by the Manager, Seattle
ACO, or using a method approved in accordance with paragraph (n)(5)
of this AD.
Restatement of AD 2003-19-08
Repetitive Inspections
(j) 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), whichever is later: Do a detailed inspection
of the body station 2598 bulkhead for discrepancies (cracking,
elongated fastener holes) of the areas specified in paragraphs
(j)(1) and (j)(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.
(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
(k) If any discrepancy is found during any inspection required
by paragraph (j) 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 any discrepancy is found and the service
bulletin specifies to contact Boeing for appropriate action: Before
further flight, repair in accordance with a method approved by the
Manager, Seattle ACO, or using a method approved in accordance with
paragraph (n)(5) of this AD.
New Requirements of This AD
Modification
(l) Before the accumulation of 20,000 total flight cycles, or
within 48 months after the effective date of this AD, 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 chord, aft inner chord, upper splice fitting,
and frame support fitting, as specified in the Accomplishment
Instructions of Boeing Service Bulletin 747-53-2473, dated March 24,
2005. Repair any cracks before further flight in accordance with the
service bulletin. Where the service bulletin 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
(n) or (n)(5) of this AD. Accomplishment of the modification
terminates the repetitive inspections required by paragraphs (f),
(h), and (j)(1) of this AD.
Inspection
(m) Within 20,000 flight cycles after the modification required
by paragraph (l) of this AD, inspect the body station 2598 bulkhead
for cracks, and repair any cracks before further flight, in
accordance with a method approved by the Manager, Seattle ACO.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) AMOCs approved previously according to AD 2000-08-21,
amendment 39-11707, and AD 2001-15-03 are approved as AMOCs for the
corresponding requirements of paragraphs (h) and (i) of this AD. (AD
2000-08-21 was superseded by AD 2001-15-03.)
(3) AMOCs approved previously according to AD 2001-14-07 are
approved as AMOCs for the corresponding requirements of paragraphs
(f) and (g) of this AD.
(4) AMOCs approved previously according to AD 2003-19-08 are
approved as AMOCs for the corresponding requirements of paragraphs
(j) and (k) of this AD.
(5) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
Issued in Renton, Washington, on September 28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-20882 Filed 10-18-05; 8:45 am]
BILLING CODE 4910-13-P
