Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, 747SR, and 747SP Series Airplanes, 12136-12140 [E7-4738]
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12136
Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27525; Directorate
Identifier 2006–NM–159–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–300,
747–400, 747–400D, 747SR, and 747SP
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
rmajette on PROD1PC67 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Boeing Model 747 airplanes. The
existing AD currently requires repetitive
inspections to detect cracks and/or
corrosion of the girt bar support fitting
at certain main entry doors (MED), and
repair or replacement of the support
fitting. The existing AD also provides
for various terminating actions for the
repetitive inspections. This proposed
AD would require the following
additional actions: An inspection, for
certain airplanes, for correct installation
of square and conical washers in the girt
bar support fitting; an inspection, for
certain other airplanes, to determine if
the washers are installed; and related
investigative and corrective action if
necessary. This proposed AD results
from a report that the square and conical
washers may be installed incorrectly in
the girt bar support fitting on airplanes
on which the support fitting was
repaired or replaced in accordance with
the requirements of the existing AD. We
are proposing this AD to detect and
correct corrosion of the girt bar support
fitting, which could result in separation
of the escape slide from the lower door
sill during deployment, and
subsequently prevent proper operation
of the escape slides at the main entry
doors during an emergency. We are also
proposing this AD to detect and correct
incorrect installation of the square and
conical washers in the girt bar support
fitting, which could result in failure of
the escape slide when deployed.
DATES: We must receive comments on
this proposed AD by April 30, 2007.
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
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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:
Patrick Gillespie, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6429; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2007–27525;
Directorate Identifier 2006–NM–159–
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 you may visit https://
dms.dot.gov.
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Fmt 4702
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Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the 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
On October 31, 1996, we issued AD
96–23–05, amendment 39–9810 (61 FR
58318, November 14, 1996), for certain
Boeing Model 747 series airplanes. That
AD requires repetitive inspections to
detect cracks and/or corrosion of the girt
bar support fitting at certain main entry
doors (MED); and repair or replacement
of the support fitting. That AD also
provides for various terminating actions
for the repetitive inspections. That AD
resulted from reports that, during
scheduled deployment tests of main
entry door slides, corrosion was found
on the floor structure supports for the
escape slides of the main deck entry
doors on these airplanes. We issued that
AD to prevent such corrosion, which
could result in separation of the escape
slide from the lower door sill during
deployment, and subsequently prevent
proper operation of the escape slides at
the main entry doors during an
emergency.
Actions Since Existing AD Was Issued
Since we issued AD 96–23–05, Boeing
has determined that the square and
conical washers may be installed
incorrectly in the girt bar support fitting
on airplanes on which the support
fitting was repaired or replaced in
accordance with Boeing Service Bulletin
747–53A2378, dated June 24, 1993;
Revision 1, dated March 10, 1994; or
Revision 2, dated July 24, 2003
(Revision 1 of the service bulletin was
referenced as the appropriate source of
service information for doing the actions
specified in AD 96–23–05).
Relevant Service Information
We have reviewed Boeing Service
Bulletin 747–53A2378, Revision 3,
dated August 11, 2005. The service
bulletin contains essentially the same
procedures for the actions described in
the earlier revisions of the service
bulletin, but Revision 3 revises the
procedures for the installation of the
square and conical washers on the girt
bar support fitting.
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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules
Revision 3 also adds actions for
airplanes on which the support fitting
was replaced or repaired in accordance
with any earlier revision of the service
bulletin:
• For Groups 7, 8, and 9 airplanes
identified in the service bulletin: Do an
inspection for correct installation of
square and conical washers in the girt
bar floor fitting, related investigative
action, and corrective actions. The
related investigative action is an
inspection of the bolts and washers for
damage. The corrective actions include
installing the square and conical
washers correctly and contacting the
manufacturer if damage is found.
• For Groups 1 through 6 airplanes
identified in the service bulletin: Do an
inspection to check if square and
conical washers are installed in the girt
bar floor fitting, related investigative
actions, and corrective actions. The
related investigative actions include
doing an inspection for correct
installation of square and conical
washers in the girt bar floor fitting and
an inspection of the bolts and washers
for damage. The corrective actions
include installing the square and
conical washers correctly and
contacting the manufacturer if damage
is found.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
rmajette on PROD1PC67 with PROPOSALS
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to develop on
other airplanes of the same type design.
For this reason, we are proposing this
AD, which would supersede AD 96–23–
05 and would retain the requirements of
the existing AD. This proposed AD
would also require the following actions
for airplanes on which the support
fitting was repaired or replaced in
accordance with Boeing Service Bulletin
747–53A2378, dated June 24, 1993;
Revision 1, dated March 10, 1994; or
Revision 2, dated July 24, 2003: An
inspection, for certain airplanes, for
correct installation of square and
conical washers in the girt bar support
fitting; an inspection, for certain other
airplanes, to determine if the washers
are installed; and related investigative
and corrective action if necessary.
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14:19 Mar 14, 2007
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Differences Between the Proposed AD
and the Service Bulletin
Although Boeing Service Bulletin
747–53A2378 specifies that operators
may contact the manufacturer if certain
damage is found, this proposed AD
would require operators to repair those
conditions using a method approved by
the FAA.
Although Boeing Service Bulletin
747–53A2378, Revision 3, specifies
doing certain actions if Boeing Service
Bulletin 747–53A2378, dated June 24,
1993; Revision 1, dated March 10, 1994;
or Revision 2, dated July 24, 2003; was
accomplished, this proposed AD would
require those actions to also be done if
Boeing Service Bulletin 747–25A2831,
dated August 29, 1991, was
accomplished. Paragraph (m) of AD 96–
23–05 allows installation of the girt bar
fitting in accordance with Boeing
Service Bulletin 747–25A2831 as an
acceptable method of compliance.
Therefore, installations done in
accordance with Boeing Service Bulletin
747–25A2831 should also be inspected
for incorrect installation of the square
and conical washers in the girt bar
support fitting.
Change to Existing AD
This proposed AD would retain all
requirements of AD 96–23–05. Since AD
96–23–05 was issued, the AD format has
been revised, and certain paragraphs
have been rearranged. As a result, the
corresponding paragraph identifiers
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
96–23–05
Note 1 .......................
paragraph (a) ............
paragraph (b) ............
paragraph (c) ............
paragraph (d) ............
paragraph (e) ............
paragraph (f) .............
paragraph (g) ............
paragraph (h) ............
paragraph (i) .............
paragraph (j) .............
paragraph (k) ............
paragraph (l) .............
paragraph (m) ...........
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Frm 00016
Fmt 4702
Corresponding
requirement in this
proposed AD
12137
Note 2 and paragraph (o) of AD 96–
23–05 have been removed from this
proposed AD. On July 10, 2002, the
FAA issued a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002),
which governs the FAA’s airworthiness
directives system. The regulation now
includes material that relates to altered
products and alternative methods of
compliance (AMOCs), as well as special
flight permits (e.g., ferry flights).
Clarification of Doors Affected by the
Proposed AD
We have also revised Note 1 of AD
96–23–05, which has the corresponding
requirement in paragraph (f) of this
proposed AD. We have added the
statement ‘‘the requirements of this AD
are also not applicable to doors on
airplanes converted to an all-cargo
configuration.’’
Explanation of Change to Applicability
We have revised the applicability of
the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models. Special freighters are
not identified in the type certificate data
sheet so the phrase ‘‘special freighters’’
has been removed from the
applicability. However, as stated
previously, we have added a statement
to exempt doors on airplanes converted
to an all-cargo configuration.
Explanation of Change Made to Existing
Requirements
We have changed all references to a
‘‘detailed visual inspection’’ in the
existing AD to ‘‘detailed inspection’’ in
this proposed AD.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
(f).
(g).
(h).
(i).
(j).
(k).
(l).
(m).
(n).
(o).
(p).
(q).
(r).
(s).
Sfmt 4702
E:\FR\FM\15MRP1.SGM
Costs of Compliance
There are about 1,012 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 per hour is $80. The
cost varies depending on the
configuration of the airplane.
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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules
ESTIMATED COSTS
Action
Work hours
Cost per airplane
Number of U.S.-registered
airplanes
Fleet cost
Inspection of MEDs (required by AD 96–23–05).
Between 88 and 102 .........
169 ....................................
Inspection for correct installation (new proposed
action).
6 ........................................
Between $7,040 and
$8,160, per inspection
cycle.
$480 ..................................
Between $1,189,760 and
$1,379,040, per inspection cycle.
Up to $81,120.
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.
rmajette on PROD1PC67 with PROPOSALS
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.
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14:19 Mar 14, 2007
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Up to 169 ..........................
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–9810 (61
FR 58318, November 14, 1996) and
adding the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2007–27525;
Directorate Identifier 2006–NM–159–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 30, 2007.
Affected ADs
(b) This AD supersedes AD 96–23–05.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–300, 747–400, 747–400D,
747SR, and 747SP series airplanes,
certificated in any category, line numbers 1
through 868 inclusive.
Unsafe Condition
(d) This AD results from reports that,
during scheduled deployment tests of main
entry door slides, corrosion was found on the
floor structure supports for the escape slides
of the main deck entry doors on these
airplanes. This AD also results from a report
that the square and conical washers may be
installed incorrectly in the girt bar support
fitting on airplanes on which the support
fitting was repaired or replaced in
accordance with the requirements of AD 96–
23–05. We are issuing this AD to detect and
correct corrosion of the girt bar support
fitting, which could result in separation of
the escape slide from the lower door sill
during deployment, and subsequently
prevent proper operation of the escape slides
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Frm 00017
Fmt 4702
Sfmt 4702
at the main entry doors during an emergency.
We are also issuing this AD to detect and
correct incorrect installation of the square
and conical washers in the girt bar support
fitting, which could result in failure of the
escape slide when deployed.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 96–23–
05 With New Service Information
Doors Exempt From/Affected by This AD
(f) The requirements of this AD are not
applicable to doors where an escape slide or
slide/raft is not installed or is not used for
passenger egress (such as a deactivated door
3, at doors 4 and/or 5 of an airplane being
operated in the ‘‘combi’’ configuration, or
any door not used for passenger egress in a
‘‘convertible’’ (an airplane configured for
quick change from passenger to cargo)). The
requirements of this AD are also not
applicable to doors on airplanes converted to
an all-cargo configuration. The requirements
of this AD become applicable at the time
when an escape slide or slide/raft is installed
on such doors, or when such doors are
activated and/or converted for passenger use.
The requirements also become applicable at
the time an airplane operating in an all-cargo
configuration is converted to a passenger or
passenger/cargo configuration.
Inspections and Corrective Actions for
Airplanes Equipped With Main Entry Door
(MED) 1
(g) For airplanes equipped with MED 1:
Prior to the accumulation of 16 years of
service since date of manufacture of the
airplane, or within 18 months after December
16, 1996 (the effective date of AD 96–23–05),
whichever occurs later, perform a detailed
inspection to detect cracking and/or
corrosion of the girt bar support fitting at the
left and right MED 1, in accordance with
Boeing Service Bulletin 747–53A2378,
Revision 1, dated March 10, 1994; or Boeing
Service Bulletin 747–53A2378, Revision 3,
dated August 11, 2005. After the effective
date of this AD, only Revision 3 may be used.
(h) If no cracking or corrosion is found
during the inspection required by paragraph
(g) of this AD, prior to further flight,
accomplish either paragraph (h)(1) or (h)(2)
of this AD, in accordance with the applicable
instructions specified in Boeing Service
Bulletin 747–53A2378, Revision 1, dated
March 10, 1994; or Boeing Service Bulletin
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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules
747–53A2378, Revision 3, dated August 11,
2005. After the effective date of this AD, only
Revision 3 may be used.
(1) Install a new fitting with new fasteners,
and reinstall the threshold assembly with
new corrosion-resistant fasteners, in
accordance with the service bulletin. After
these actions are accomplished, no further
action is required by paragraph (h) of this
AD; or
(2) Reinstall the threshold assembly with
corrosion-resistant fasteners, in accordance
with the service bulletin. Thereafter, repeat
the inspection required by paragraph (g) of
this AD at intervals not to exceed 6 years.
(i) If any cracking is found during the
inspection required by paragraph (g) or (h)(2)
of this AD, prior to further flight, install a
new fitting with new fasteners, and reinstall
the threshold assembly with new corrosionresistant fasteners, in accordance with Boeing
Service Bulletin 747–53A2378, Revision 1,
dated March 10, 1994; or Boeing Service
Bulletin 747–53A2378, Revision 3, dated
August 11, 2005. After the effective date of
this AD, only Revision 3 may be used. After
these actions are accomplished, no further
action is required by this paragraph.
(j) If any corrosion is found during the
inspection required by paragraph (g) or (h)(2)
of this AD, prior to further flight, accomplish
either paragraph (j)(1) or (j)(2) of this AD, in
accordance with Boeing Service Bulletin
747–53A2378, Revision 1, dated March 10,
1994; or Boeing Service Bulletin 747–
53A2378, Revision 3, dated August 11, 2005.
After the effective date of this AD, only
Revision 3 may be used.
(1) Install a new fitting with new fasteners,
and reinstall the threshold assembly with
new corrosion-resistant fasteners in
accordance with the service bulletin. After
these actions are accomplished, no further
action is required by this paragraph; or
(2) Blend out corrosion in accordance with
the service bulletin.
(i) If blend out of corrosion is beyond 10
percent of original thickness or any crack is
found during accomplishment of the blend
out procedures, install a new fitting with new
fasteners, and reinstall the threshold
assembly with new corrosion-resistant
fasteners, in accordance with the service
bulletin. After these actions are
accomplished, no further action is required
by this paragraph.
(ii) If blend out of corrosion does not
exceed 10 percent of original material
thickness, accomplish either paragraph
(j)(2)(ii)(A) or (j)(2)(ii)(B) of this AD:
(A) Install a new fitting with new fasteners,
and reinstall threshold assembly with new
corrosion-resistant fasteners, in accordance
with the service bulletin. After these actions
are accomplished, no further action is
required by this paragraph; or
(B) Install the repaired fitting with new
fasteners and reinstall the threshold assembly
with corrosion-resistant fasteners, in
accordance with the service bulletin.
Thereafter, repeat the inspection and
applicable corrective actions required by
paragraph (g) of this AD at intervals not to
exceed 6 years.
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14:19 Mar 14, 2007
Jkt 211001
Inspections and Corrective Actions for
Airplanes Equipped With MED 2, 4, and/or
5 (MED 2, 3, and/or 4 on Model 747SP Series
Airplanes)
(k) For airplanes equipped with MED 2, 4,
and/or 5 (MED 2, 3, and/or 4 on Model 747SP
series airplanes): Prior to the accumulation of
10 years of service since date of manufacture
of the airplane, or within 18 months after
December 16, 1996, whichever occurs later,
perform a detailed inspection to detect
cracking and/or corrosion of the girt bar
support fitting at the left and right MED 2,
4, and 5 (MED 2, 3, and 4 on Model 747SP
series airplanes), in accordance with Boeing
Service Bulletin 747–53A2378, Revision 1,
dated March 10, 1994; or Boeing Service
Bulletin 747–53A2378, Revision 3, dated
August 11, 2005. After the effective date of
this AD, only Revision 3 may be used.
(l) If no cracking or corrosion is found
during the inspection required by paragraph
(k) of this AD, prior to further flight,
accomplish either paragraph (l)(1) or (l)(2) of
this AD, in accordance with the applicable
instructions in Boeing Service Bulletin 747–
53A2378, Revision 1, dated March 10, 1994;
or Boeing Service Bulletin 747–53A2378,
Revision 3, dated August 11, 2005. After the
effective date of this AD, only Revision 3 may
be used.
(1) Remove the inspected fitting and
reinstall it with a new coat of primer and
new fasteners; and reinstall the threshold
assembly with new corrosion-resistant
fasteners; in accordance with the service
bulletin. After these actions are
accomplished, no further action is required
by this paragraph; or
(2) Reinstall the serrated plate assembly
and the girt bar floor fitting with corrosionresistant fasteners, in accordance with the
service bulletin. Thereafter, repeat the
inspection required by paragraph (k) of this
AD at intervals not to exceed 6 years.
(m) If any cracking is found during the
inspection required by paragraph (k) or (l)(2)
of this AD, prior to further flight, install a
new fitting with new fasteners, and reinstall
the threshold assembly with new corrosionresistant fasteners, in accordance with Boeing
Service Bulletin 747–53A2378, Revision 1,
dated March 10, 1994; or Boeing Service
Bulletin 747–53A2378, Revision 3, dated
August 11, 2005. After the effective date of
this AD, only Revision 3 may be used. After
these actions are accomplished, no further
action is required by this paragraph.
(n) If any corrosion is found during the
inspection required by paragraph (k) or (l)(2)
of this AD, prior to further flight, accomplish
either paragraph (n)(1) or (n)(2) of this AD,
in accordance with Boeing Service Bulletin
747–53A2378, Revision 1, dated March 10,
1994; or Boeing Service Bulletin 747–
53A2378, Revision 3, dated August 11, 2005.
After the effective date of this AD, only
Revision 3 may be used.
(1) Install a new fitting with new fasteners,
and reinstall the threshold assembly with
new corrosion-resistant fasteners, in
accordance with the service bulletin. After
these actions are accomplished, no further
action is required by this paragraph; or
(2) Blend out corrosion in accordance with
the service bulletin.
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Fmt 4702
Sfmt 4702
12139
(i) If blend out of corrosion is beyond 10
percent of original thickness or any crack is
found during accomplishment of the blend
out procedures, install a new fitting with new
fasteners, and reinstall the threshold
assembly with new corrosion-resistant
fasteners, in accordance with the service
bulletin. After these actions are
accomplished, no further action is required
by this paragraph.
(ii) If blend out of corrosion does not
exceed 10 percent of original material
thickness, install the repaired fitting with
new fasteners, and reinstall the threshold
assembly with new corrosion-resistant
fasteners, in accordance with the service
bulletin. After these actions are
accomplished, no further action is required
by this paragraph.
(o) For airplanes equipped with main entry
door (MED) 3 (this paragraph does not apply
to Model 747SP series airplanes): Prior to the
accumulation of 16 years of service since
date of manufacture of the airplane, or within
18 months after December 16, 1996,
whichever occurs later, perform a detailed
inspection to detect cracking and/or
corrosion of the girt bar support angles at the
left and right MED 3, in accordance with
Boeing Service Bulletin 747–53A2378,
Revision 1, dated March 10, 1994; or Boeing
Service Bulletin 747–53A2378, Revision 3,
dated August 11, 2005. After the effective
date of this AD, only Revision 3 may be used.
(p) If no cracking or corrosion is found
during the inspection required by paragraph
(o) of this AD, prior to further flight,
accomplish either paragraph (p)(1) or (p)(2)
of this AD in accordance with the applicable
instructions in Boeing Service Bulletin 747–
53A2378, Revision 1, dated March 10, 1994;
or Boeing Service Bulletin 747–53A2378,
Revision 3, dated August 11, 2005. After the
effective date of this AD, only Revision 3 may
be used.
(1) Remove the inspected angle and
reinstall it with a new coat of primer and
new fasteners; and reinstall the threshold
assembly with new corrosion-resistant
fasteners; in accordance with the service
bulletin. After these actions are
accomplished, no further action is required
by this paragraph; or
(2) Reinstall the corner scuff plate and the
threshold apron with corrosion-resistant
fasteners, in accordance with the service
bulletin. Thereafter, repeat the inspection
required by paragraph (o) of this AD at
intervals not to exceed 6 years.
(q) If any crack common to the support
angles is found during the inspection
required by paragraph (o) or (p)(2) of this AD,
prior to further flight, accomplish the actions
specified in paragraph (q)(1) or (q)(2), as
applicable, in accordance with Boeing
Service Bulletin 747–53A2378, Revision 1,
dated March 10, 1994; or Boeing Service
Bulletin 747–53A2378, Revision 3, dated
August 11, 2005. After the effective date of
this AD, only Revision 3 may be used:
(1) Install the new angles with new
fasteners, and reinstall the threshold
assembly with new corrosion-resistant
fasteners. After these actions are
accomplished, no further action is required
by this paragraph of this AD; or
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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules
rmajette on PROD1PC67 with PROPOSALS
(2) For any cracking found only in the
corner casting as specified in the service
bulletin, accomplish either paragraph (q)(2)(i)
or (q)(2)(ii) prior to further flight:
(i) Replace the corner casting in accordance
with the service bulletin; or
(ii) Repair the cracked part in accordance
with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO),
FAA, Transport Airplane Directorate. Refer to
paragraph (w) of this AD for the appropriate
procedure for seeking such an approval.
(This option is provided in order to give
operators time to obtain a replacement corner
casing without grounding an airplane.) This
repair is considered temporary action only;
replacement of the corner casting eventually
must be accomplished in accordance with a
schedule prescribed by the Manager, Seattle
ACO.
(r) If any corrosion is found during the
inspection required by paragraph (o) of this
AD, prior to further flight, accomplish either
paragraph (r)(1) or (r)(2) of this AD, in
accordance with Boeing Service Bulletin
747–53A2378, Revision 1, dated March 10,
1994; or Boeing Service Bulletin 747–
53A2378, Revision 3, dated August 11, 2005.
After the effective date of this AD, only
Revision 3 may be used.
(1) Install the new angles with new
fasteners, and reinstall the threshold
assembly with new corrosion-resistant
fasteners, in accordance with the service
bulletin. After these actions are
accomplished, no further action is required
by this paragraph; or
(2) Blend out corrosion in accordance with
the service bulletin.
(i) If blend out of corrosion is beyond 10
percent of original thickness, or if any crack
common to the support angles is found
during accomplishment of the blend out
procedures, install the new angles with new
fasteners, and reinstall the threshold
assembly with new corrosion-resistant
fasteners, in accordance with the service
bulletin. After these actions are
accomplished, no further action is required
by this paragraph.
(ii) If blend out of corrosion does not
exceed 10 percent of original material
thickness, install the repaired angles with
new fasteners, and reinstall the threshold
assembly with new corrosion-resistant
fasteners, in accordance with the service
bulletin. After these actions are
accomplished, no further action is required
by this paragraph.
53A2378, Revision 3, dated August 11, 2005,
on which the support fitting was replaced or
repaired in accordance with Boeing Service
Bulletin 747–53A2378, dated June 24, 1993;
Revision 1, dated March 10, 1994; or
Revision 2, dated July 24, 2003; or Boeing
Service Bulletin 747–25A2831, dated August
29, 1991: Within 18 months after the effective
date of this AD, do a general visual
inspection for correct installation of square
and conical washers in the girt bar floor
fittings, and, before further flight, do all
applicable related investigative and
corrective actions. Do all actions in
accordance with Figure 18 and the applicable
steps specified on page 52 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2378, Revision 3,
dated August 11, 2005, except as provided by
paragraph (v) of this AD.
(u) For Groups 1 through 6 airplanes
identified in Boeing Service Bulletin 747–
53A2378, Revision 3, dated August 11, 2005,
on which the support fitting was replaced or
repaired in accordance with Boeing Service
Bulletin 747–53A2378, dated June 24, 1993;
Revision 1, dated March 10, 1994; or
Revision 2, dated July 24, 2003; or with
Boeing Service Bulletin 747–25A2831, dated
August 29, 1991: Within 18 months after the
effective date of this AD, do a general visual
inspection to determine if square and conical
washers are installed in the girt bar floor
fittings, and before further flight, do all
applicable related investigative and
corrective actions. Do all actions in
accordance with Figure 18 and the applicable
steps specified on pages 52 and 53 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2378, Revision 3,
dated August 11, 2005, except as provided by
paragraph (v) of this AD.
(v) If any damage is found during any
inspection required by paragraphs (t) and (u)
of this AD, and the bulletin specifies
contacting Boeing for appropriate action:
Before further flight, do the repair using a
method approved by the Manager, Seattle
ACO, FAA, or in accordance with data
meeting the certification basis of the airplane
approved by an Authorized Representative
for the Boeing Commercial Airplanes
Delegation Option Authorization 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.
Actions Accomplished According to Previous
Issue of Service Bulletin
(s) Installation of a girt bar support fitting
in accordance with Boeing Service Bulletin
747–25A2831, dated August 29, 1991, before
the effective date of this AD, is considered
acceptable for compliance with the
corresponding requirements of paragraphs
(h), (i), (j), (l), (m), and (n) of this AD for each
affected fitting location.
Alternative Methods of Compliance
(AMOCs)
New Requirements of This AD
Inspections for the Washers and Related
Investigative/Corrective Actions
(t) For Groups 7, 8, and 9 airplanes
identified in Boeing Service Bulletin 747–
VerDate Aug<31>2005
14:19 Mar 14, 2007
Jkt 211001
(w)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 96–23–05, are approved
as AMOCs for the corresponding provisions
of this AD.
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
Issued in Renton, Washington, on March 7,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–4738 Filed 3–14–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF DEFENSE
Department of the Army
32 CFR Part 635
[Docket No. USA–2007–0007]
RIN 0702–AA56
Law Enforcement Reporting
Department of the Army, DoD.
Proposed rule; request for
comments.
AGENCY:
ACTION:
SUMMARY: The Department of the Army
proposes to amend its regulation
concerning law enforcement reporting.
The regulation prescribes policies and
procedures on preparing, reporting,
using, retaining, and disposing of
Military Police Reports. The regulation
prescribes policies and procedures for
offense reporting and the release of law
enforcement information.
DATES: Consideration will be given to all
comments received by April 16, 2007.
ADDRESSES: You may submit comments,
identified by 32 CFR Part 635, Docket
No. USA–2007–0007 and/or RIN 0702–
AA56, by any of the following methods:
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
• Mail: Federal Docket Management
System Office, 1160 Defense Pentagon,
Washington, DC 20301–1160.
Instructions: All submissions received
must include the agency name and
docket number or Regulatory
Information Number (RIN) for this
Federal Register document. The general
policy for comments and other
submissions from members of the public
is to make these submissions available
for public viewing on the Internet at
https://www.regulations.gov as they are
received without change, including any
personal identifiers or contact
information.
FOR FURTHER INFORMATION CONTACT:
James Crumley, (703) 692–6721.
SUPPLEMENTARY INFORMATION:
A. Background
In the December 9, 2005 issue of the
Federal Register (70 FR 73181) the
Department of the Army published a
proposed rule, amending 32 CFR part
E:\FR\FM\15MRP1.SGM
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]]>Agencies
[Federal Register Volume 72, Number 50 (Thursday, March 15, 2007)]
[Proposed Rules]
[Pages 12136-12140]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4738]
[[Page 12136]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27525; Directorate Identifier 2006-NM-159-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, 747SR, and
747SP Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Boeing Model 747 airplanes. The
existing AD currently requires repetitive inspections to detect cracks
and/or corrosion of the girt bar support fitting at certain main entry
doors (MED), and repair or replacement of the support fitting. The
existing AD also provides for various terminating actions for the
repetitive inspections. This proposed AD would require the following
additional actions: An inspection, for certain airplanes, for correct
installation of square and conical washers in the girt bar support
fitting; an inspection, for certain other airplanes, to determine if
the washers are installed; and related investigative and corrective
action if necessary. This proposed AD results from a report that the
square and conical washers may be installed incorrectly in the girt bar
support fitting on airplanes on which the support fitting was repaired
or replaced in accordance with the requirements of the existing AD. We
are proposing this AD to detect and correct corrosion of the girt bar
support fitting, which could result in separation of the escape slide
from the lower door sill during deployment, and subsequently prevent
proper operation of the escape slides at the main entry doors during an
emergency. We are also proposing this AD to detect and correct
incorrect installation of the square and conical washers in the girt
bar support fitting, which could result in failure of the escape slide
when deployed.
DATES: We must receive comments on this proposed AD by April 30, 2007.
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: Patrick Gillespie, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6429; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2007-27525; Directorate Identifier 2006-NM-159-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 you
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 (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
On October 31, 1996, we issued AD 96-23-05, amendment 39-9810 (61
FR 58318, November 14, 1996), for certain Boeing Model 747 series
airplanes. That AD requires repetitive inspections to detect cracks
and/or corrosion of the girt bar support fitting at certain main entry
doors (MED); and repair or replacement of the support fitting. That AD
also provides for various terminating actions for the repetitive
inspections. That AD resulted from reports that, during scheduled
deployment tests of main entry door slides, corrosion was found on the
floor structure supports for the escape slides of the main deck entry
doors on these airplanes. We issued that AD to prevent such corrosion,
which could result in separation of the escape slide from the lower
door sill during deployment, and subsequently prevent proper operation
of the escape slides at the main entry doors during an emergency.
Actions Since Existing AD Was Issued
Since we issued AD 96-23-05, Boeing has determined that the square
and conical washers may be installed incorrectly in the girt bar
support fitting on airplanes on which the support fitting was repaired
or replaced in accordance with Boeing Service Bulletin 747-53A2378,
dated June 24, 1993; Revision 1, dated March 10, 1994; or Revision 2,
dated July 24, 2003 (Revision 1 of the service bulletin was referenced
as the appropriate source of service information for doing the actions
specified in AD 96-23-05).
Relevant Service Information
We have reviewed Boeing Service Bulletin 747-53A2378, Revision 3,
dated August 11, 2005. The service bulletin contains essentially the
same procedures for the actions described in the earlier revisions of
the service bulletin, but Revision 3 revises the procedures for the
installation of the square and conical washers on the girt bar support
fitting.
[[Page 12137]]
Revision 3 also adds actions for airplanes on which the support
fitting was replaced or repaired in accordance with any earlier
revision of the service bulletin:
For Groups 7, 8, and 9 airplanes identified in the service
bulletin: Do an inspection for correct installation of square and
conical washers in the girt bar floor fitting, related investigative
action, and corrective actions. The related investigative action is an
inspection of the bolts and washers for damage. The corrective actions
include installing the square and conical washers correctly and
contacting the manufacturer if damage is found.
For Groups 1 through 6 airplanes identified in the service
bulletin: Do an inspection to check if square and conical washers are
installed in the girt bar floor fitting, related investigative actions,
and corrective actions. The related investigative actions include doing
an inspection for correct installation of square and conical washers in
the girt bar floor fitting and an inspection of the bolts and washers
for damage. The corrective actions include installing the square and
conical washers correctly and contacting the manufacturer if damage is
found.
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 develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 96-23-05 and would retain the requirements of the
existing AD. This proposed AD would also require the following actions
for airplanes on which the support fitting was repaired or replaced in
accordance with Boeing Service Bulletin 747-53A2378, dated June 24,
1993; Revision 1, dated March 10, 1994; or Revision 2, dated July 24,
2003: An inspection, for certain airplanes, for correct installation of
square and conical washers in the girt bar support fitting; an
inspection, for certain other airplanes, to determine if the washers
are installed; and related investigative and corrective action if
necessary.
Differences Between the Proposed AD and the Service Bulletin
Although Boeing Service Bulletin 747-53A2378 specifies that
operators may contact the manufacturer if certain damage is found, this
proposed AD would require operators to repair those conditions using a
method approved by the FAA.
Although Boeing Service Bulletin 747-53A2378, Revision 3, specifies
doing certain actions if Boeing Service Bulletin 747-53A2378, dated
June 24, 1993; Revision 1, dated March 10, 1994; or Revision 2, dated
July 24, 2003; was accomplished, this proposed AD would require those
actions to also be done if Boeing Service Bulletin 747-25A2831, dated
August 29, 1991, was accomplished. Paragraph (m) of AD 96-23-05 allows
installation of the girt bar fitting in accordance with Boeing Service
Bulletin 747-25A2831 as an acceptable method of compliance. Therefore,
installations done in accordance with Boeing Service Bulletin 747-
25A2831 should also be inspected for incorrect installation of the
square and conical washers in the girt bar support fitting.
Change to Existing AD
This proposed AD would retain all requirements of AD 96-23-05.
Since AD 96-23-05 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement
Requirement in AD 96-23-05 in this proposed AD
------------------------------------------------------------------------
Note 1.................................... paragraph (f).
paragraph (a)............................. paragraph (g).
paragraph (b)............................. paragraph (h).
paragraph (c)............................. paragraph (i).
paragraph (d)............................. paragraph (j).
paragraph (e)............................. paragraph (k).
paragraph (f)............................. paragraph (l).
paragraph (g)............................. paragraph (m).
paragraph (h)............................. paragraph (n).
paragraph (i)............................. paragraph (o).
paragraph (j)............................. paragraph (p).
paragraph (k)............................. paragraph (q).
paragraph (l)............................. paragraph (r).
paragraph (m)............................. paragraph (s).
------------------------------------------------------------------------
Note 2 and paragraph (o) of AD 96-23-05 have been removed from this
proposed AD. On July 10, 2002, the FAA issued a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002), which governs the FAA's
airworthiness directives system. The regulation now includes material
that relates to altered products and alternative methods of compliance
(AMOCs), as well as special flight permits (e.g., ferry flights).
Clarification of Doors Affected by the Proposed AD
We have also revised Note 1 of AD 96-23-05, which has the
corresponding requirement in paragraph (f) of this proposed AD. We have
added the statement ``the requirements of this AD are also not
applicable to doors on airplanes converted to an all-cargo
configuration.''
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models. Special freighters are not
identified in the type certificate data sheet so the phrase ``special
freighters'' has been removed from the applicability. However, as
stated previously, we have added a statement to exempt doors on
airplanes converted to an all-cargo configuration.
Explanation of Change Made to Existing Requirements
We have changed all references to a ``detailed visual inspection''
in the existing AD to ``detailed inspection'' in this proposed AD.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Costs of Compliance
There are about 1,012 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
per hour is $80. The cost varies depending on the configuration of the
airplane.
[[Page 12138]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Cost per airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
Inspection of MEDs (required by Between 88 and 102 Between $7,040 and 169............... Between $1,189,760
AD 96-23-05). $8,160, per and $1,379,040,
inspection cycle. per inspection
cycle.
Inspection for correct 6................. $480.............. Up to 169......... Up to $81,120.
installation (new 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 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 39-9810 (61 FR 58318, November 14, 1996) and adding
the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2007-27525; Directorate Identifier 2006-NM-
159-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 30,
2007.
Affected ADs
(b) This AD supersedes AD 96-23-05.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, 747SR, and
747SP series airplanes, certificated in any category, line numbers 1
through 868 inclusive.
Unsafe Condition
(d) This AD results from reports that, during scheduled
deployment tests of main entry door slides, corrosion was found on
the floor structure supports for the escape slides of the main deck
entry doors on these airplanes. This AD also results from a report
that the square and conical washers may be installed incorrectly in
the girt bar support fitting on airplanes on which the support
fitting was repaired or replaced in accordance with the requirements
of AD 96-23-05. We are issuing this AD to detect and correct
corrosion of the girt bar support fitting, which could result in
separation of the escape slide from the lower door sill during
deployment, and subsequently prevent proper operation of the escape
slides at the main entry doors during an emergency. We are also
issuing this AD to detect and correct incorrect installation of the
square and conical washers in the girt bar support fitting, which
could result in failure of the escape slide when deployed.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 96-23-05 With New Service Information
Doors Exempt From/Affected by This AD
(f) The requirements of this AD are not applicable to doors
where an escape slide or slide/raft is not installed or is not used
for passenger egress (such as a deactivated door 3, at doors 4 and/
or 5 of an airplane being operated in the ``combi'' configuration,
or any door not used for passenger egress in a ``convertible'' (an
airplane configured for quick change from passenger to cargo)). The
requirements of this AD are also not applicable to doors on
airplanes converted to an all-cargo configuration. The requirements
of this AD become applicable at the time when an escape slide or
slide/raft is installed on such doors, or when such doors are
activated and/or converted for passenger use. The requirements also
become applicable at the time an airplane operating in an all-cargo
configuration is converted to a passenger or passenger/cargo
configuration.
Inspections and Corrective Actions for Airplanes Equipped With Main
Entry Door (MED) 1
(g) For airplanes equipped with MED 1: Prior to the accumulation
of 16 years of service since date of manufacture of the airplane, or
within 18 months after December 16, 1996 (the effective date of AD
96-23-05), whichever occurs later, perform a detailed inspection to
detect cracking and/or corrosion of the girt bar support fitting at
the left and right MED 1, in accordance with Boeing Service Bulletin
747-53A2378, Revision 1, dated March 10, 1994; or Boeing Service
Bulletin 747-53A2378, Revision 3, dated August 11, 2005. After the
effective date of this AD, only Revision 3 may be used.
(h) If no cracking or corrosion is found during the inspection
required by paragraph (g) of this AD, prior to further flight,
accomplish either paragraph (h)(1) or (h)(2) of this AD, in
accordance with the applicable instructions specified in Boeing
Service Bulletin 747-53A2378, Revision 1, dated March 10, 1994; or
Boeing Service Bulletin
[[Page 12139]]
747-53A2378, Revision 3, dated August 11, 2005. After the effective
date of this AD, only Revision 3 may be used.
(1) Install a new fitting with new fasteners, and reinstall the
threshold assembly with new corrosion-resistant fasteners, in
accordance with the service bulletin. After these actions are
accomplished, no further action is required by paragraph (h) of this
AD; or
(2) Reinstall the threshold assembly with corrosion-resistant
fasteners, in accordance with the service bulletin. Thereafter,
repeat the inspection required by paragraph (g) of this AD at
intervals not to exceed 6 years.
(i) If any cracking is found during the inspection required by
paragraph (g) or (h)(2) of this AD, prior to further flight, install
a new fitting with new fasteners, and reinstall the threshold
assembly with new corrosion-resistant fasteners, in accordance with
Boeing Service Bulletin 747-53A2378, Revision 1, dated March 10,
1994; or Boeing Service Bulletin 747-53A2378, Revision 3, dated
August 11, 2005. After the effective date of this AD, only Revision
3 may be used. After these actions are accomplished, no further
action is required by this paragraph.
(j) If any corrosion is found during the inspection required by
paragraph (g) or (h)(2) of this AD, prior to further flight,
accomplish either paragraph (j)(1) or (j)(2) of this AD, in
accordance with Boeing Service Bulletin 747-53A2378, Revision 1,
dated March 10, 1994; or Boeing Service Bulletin 747-53A2378,
Revision 3, dated August 11, 2005. After the effective date of this
AD, only Revision 3 may be used.
(1) Install a new fitting with new fasteners, and reinstall the
threshold assembly with new corrosion-resistant fasteners in
accordance with the service bulletin. After these actions are
accomplished, no further action is required by this paragraph; or
(2) Blend out corrosion in accordance with the service bulletin.
(i) If blend out of corrosion is beyond 10 percent of original
thickness or any crack is found during accomplishment of the blend
out procedures, install a new fitting with new fasteners, and
reinstall the threshold assembly with new corrosion-resistant
fasteners, in accordance with the service bulletin. After these
actions are accomplished, no further action is required by this
paragraph.
(ii) If blend out of corrosion does not exceed 10 percent of
original material thickness, accomplish either paragraph
(j)(2)(ii)(A) or (j)(2)(ii)(B) of this AD:
(A) Install a new fitting with new fasteners, and reinstall
threshold assembly with new corrosion-resistant fasteners, in
accordance with the service bulletin. After these actions are
accomplished, no further action is required by this paragraph; or
(B) Install the repaired fitting with new fasteners and
reinstall the threshold assembly with corrosion-resistant fasteners,
in accordance with the service bulletin. Thereafter, repeat the
inspection and applicable corrective actions required by paragraph
(g) of this AD at intervals not to exceed 6 years.
Inspections and Corrective Actions for Airplanes Equipped With MED
2, 4, and/or 5 (MED 2, 3, and/or 4 on Model 747SP Series Airplanes)
(k) For airplanes equipped with MED 2, 4, and/or 5 (MED 2, 3,
and/or 4 on Model 747SP series airplanes): Prior to the accumulation
of 10 years of service since date of manufacture of the airplane, or
within 18 months after December 16, 1996, whichever occurs later,
perform a detailed inspection to detect cracking and/or corrosion of
the girt bar support fitting at the left and right MED 2, 4, and 5
(MED 2, 3, and 4 on Model 747SP series airplanes), in accordance
with Boeing Service Bulletin 747-53A2378, Revision 1, dated March
10, 1994; or Boeing Service Bulletin 747-53A2378, Revision 3, dated
August 11, 2005. After the effective date of this AD, only Revision
3 may be used.
(l) If no cracking or corrosion is found during the inspection
required by paragraph (k) of this AD, prior to further flight,
accomplish either paragraph (l)(1) or (l)(2) of this AD, in
accordance with the applicable instructions in Boeing Service
Bulletin 747-53A2378, Revision 1, dated March 10, 1994; or Boeing
Service Bulletin 747-53A2378, Revision 3, dated August 11, 2005.
After the effective date of this AD, only Revision 3 may be used.
(1) Remove the inspected fitting and reinstall it with a new
coat of primer and new fasteners; and reinstall the threshold
assembly with new corrosion-resistant fasteners; in accordance with
the service bulletin. After these actions are accomplished, no
further action is required by this paragraph; or
(2) Reinstall the serrated plate assembly and the girt bar floor
fitting with corrosion-resistant fasteners, in accordance with the
service bulletin. Thereafter, repeat the inspection required by
paragraph (k) of this AD at intervals not to exceed 6 years.
(m) If any cracking is found during the inspection required by
paragraph (k) or (l)(2) of this AD, prior to further flight, install
a new fitting with new fasteners, and reinstall the threshold
assembly with new corrosion-resistant fasteners, in accordance with
Boeing Service Bulletin 747-53A2378, Revision 1, dated March 10,
1994; or Boeing Service Bulletin 747-53A2378, Revision 3, dated
August 11, 2005. After the effective date of this AD, only Revision
3 may be used. After these actions are accomplished, no further
action is required by this paragraph.
(n) If any corrosion is found during the inspection required by
paragraph (k) or (l)(2) of this AD, prior to further flight,
accomplish either paragraph (n)(1) or (n)(2) of this AD, in
accordance with Boeing Service Bulletin 747-53A2378, Revision 1,
dated March 10, 1994; or Boeing Service Bulletin 747-53A2378,
Revision 3, dated August 11, 2005. After the effective date of this
AD, only Revision 3 may be used.
(1) Install a new fitting with new fasteners, and reinstall the
threshold assembly with new corrosion-resistant fasteners, in
accordance with the service bulletin. After these actions are
accomplished, no further action is required by this paragraph; or
(2) Blend out corrosion in accordance with the service bulletin.
(i) If blend out of corrosion is beyond 10 percent of original
thickness or any crack is found during accomplishment of the blend
out procedures, install a new fitting with new fasteners, and
reinstall the threshold assembly with new corrosion-resistant
fasteners, in accordance with the service bulletin. After these
actions are accomplished, no further action is required by this
paragraph.
(ii) If blend out of corrosion does not exceed 10 percent of
original material thickness, install the repaired fitting with new
fasteners, and reinstall the threshold assembly with new corrosion-
resistant fasteners, in accordance with the service bulletin. After
these actions are accomplished, no further action is required by
this paragraph.
(o) For airplanes equipped with main entry door (MED) 3 (this
paragraph does not apply to Model 747SP series airplanes): Prior to
the accumulation of 16 years of service since date of manufacture of
the airplane, or within 18 months after December 16, 1996, whichever
occurs later, perform a detailed inspection to detect cracking and/
or corrosion of the girt bar support angles at the left and right
MED 3, in accordance with Boeing Service Bulletin 747-53A2378,
Revision 1, dated March 10, 1994; or Boeing Service Bulletin 747-
53A2378, Revision 3, dated August 11, 2005. After the effective date
of this AD, only Revision 3 may be used.
(p) If no cracking or corrosion is found during the inspection
required by paragraph (o) of this AD, prior to further flight,
accomplish either paragraph (p)(1) or (p)(2) of this AD in
accordance with the applicable instructions in Boeing Service
Bulletin 747-53A2378, Revision 1, dated March 10, 1994; or Boeing
Service Bulletin 747-53A2378, Revision 3, dated August 11, 2005.
After the effective date of this AD, only Revision 3 may be used.
(1) Remove the inspected angle and reinstall it with a new coat
of primer and new fasteners; and reinstall the threshold assembly
with new corrosion-resistant fasteners; in accordance with the
service bulletin. After these actions are accomplished, no further
action is required by this paragraph; or
(2) Reinstall the corner scuff plate and the threshold apron
with corrosion-resistant fasteners, in accordance with the service
bulletin. Thereafter, repeat the inspection required by paragraph
(o) of this AD at intervals not to exceed 6 years.
(q) If any crack common to the support angles is found during
the inspection required by paragraph (o) or (p)(2) of this AD, prior
to further flight, accomplish the actions specified in paragraph
(q)(1) or (q)(2), as applicable, in accordance with Boeing Service
Bulletin 747-53A2378, Revision 1, dated March 10, 1994; or Boeing
Service Bulletin 747-53A2378, Revision 3, dated August 11, 2005.
After the effective date of this AD, only Revision 3 may be used:
(1) Install the new angles with new fasteners, and reinstall the
threshold assembly with new corrosion-resistant fasteners. After
these actions are accomplished, no further action is required by
this paragraph of this AD; or
[[Page 12140]]
(2) For any cracking found only in the corner casting as
specified in the service bulletin, accomplish either paragraph
(q)(2)(i) or (q)(2)(ii) prior to further flight:
(i) Replace the corner casting in accordance with the service
bulletin; or
(ii) Repair the cracked part in accordance with a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA, Transport Airplane Directorate. Refer to paragraph (w)
of this AD for the appropriate procedure for seeking such an
approval. (This option is provided in order to give operators time
to obtain a replacement corner casing without grounding an
airplane.) This repair is considered temporary action only;
replacement of the corner casting eventually must be accomplished in
accordance with a schedule prescribed by the Manager, Seattle ACO.
(r) If any corrosion is found during the inspection required by
paragraph (o) of this AD, prior to further flight, accomplish either
paragraph (r)(1) or (r)(2) of this AD, in accordance with Boeing
Service Bulletin 747-53A2378, Revision 1, dated March 10, 1994; or
Boeing Service Bulletin 747-53A2378, Revision 3, dated August 11,
2005. After the effective date of this AD, only Revision 3 may be
used.
(1) Install the new angles with new fasteners, and reinstall the
threshold assembly with new corrosion-resistant fasteners, in
accordance with the service bulletin. After these actions are
accomplished, no further action is required by this paragraph; or
(2) Blend out corrosion in accordance with the service bulletin.
(i) If blend out of corrosion is beyond 10 percent of original
thickness, or if any crack common to the support angles is found
during accomplishment of the blend out procedures, install the new
angles with new fasteners, and reinstall the threshold assembly with
new corrosion-resistant fasteners, in accordance with the service
bulletin. After these actions are accomplished, no further action is
required by this paragraph.
(ii) If blend out of corrosion does not exceed 10 percent of
original material thickness, install the repaired angles with new
fasteners, and reinstall the threshold assembly with new corrosion-
resistant fasteners, in accordance with the service bulletin. After
these actions are accomplished, no further action is required by
this paragraph.
Actions Accomplished According to Previous Issue of Service
Bulletin
(s) Installation of a girt bar support fitting in accordance
with Boeing Service Bulletin 747-25A2831, dated August 29, 1991,
before the effective date of this AD, is considered acceptable for
compliance with the corresponding requirements of paragraphs (h),
(i), (j), (l), (m), and (n) of this AD for each affected fitting
location.
New Requirements of This AD
Inspections for the Washers and Related Investigative/Corrective
Actions
(t) For Groups 7, 8, and 9 airplanes identified in Boeing
Service Bulletin 747-53A2378, Revision 3, dated August 11, 2005, on
which the support fitting was replaced or repaired in accordance
with Boeing Service Bulletin 747-53A2378, dated June 24, 1993;
Revision 1, dated March 10, 1994; or Revision 2, dated July 24,
2003; or Boeing Service Bulletin 747-25A2831, dated August 29, 1991:
Within 18 months after the effective date of this AD, do a general
visual inspection for correct installation of square and conical
washers in the girt bar floor fittings, and, before further flight,
do all applicable related investigative and corrective actions. Do
all actions in accordance with Figure 18 and the applicable steps
specified on page 52 of the Accomplishment Instructions of Boeing
Service Bulletin 747-53A2378, Revision 3, dated August 11, 2005,
except as provided by paragraph (v) of this AD.
(u) For Groups 1 through 6 airplanes identified in Boeing
Service Bulletin 747-53A2378, Revision 3, dated August 11, 2005, on
which the support fitting was replaced or repaired in accordance
with Boeing Service Bulletin 747-53A2378, dated June 24, 1993;
Revision 1, dated March 10, 1994; or Revision 2, dated July 24,
2003; or with Boeing Service Bulletin 747-25A2831, dated August 29,
1991: Within 18 months after the effective date of this AD, do a
general visual inspection to determine if square and conical washers
are installed in the girt bar floor fittings, and before further
flight, do all applicable related investigative and corrective
actions. Do all actions in accordance with Figure 18 and the
applicable steps specified on pages 52 and 53 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2378, Revision 3,
dated August 11, 2005, except as provided by paragraph (v) of this
AD.
(v) If any damage is found during any inspection required by
paragraphs (t) and (u) of this AD, and the bulletin specifies
contacting Boeing for appropriate action: Before further flight, do
the repair using a method approved by the Manager, Seattle ACO, FAA,
or in accordance with data meeting the certification basis of the
airplane approved by an Authorized Representative for the Boeing
Commercial Airplanes Delegation Option Authorization 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.
Alternative Methods of Compliance (AMOCs)
(w)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 96-23-05,
are approved as AMOCs for the corresponding provisions of this AD.
Issued in Renton, Washington, on March 7, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-4738 Filed 3-14-07; 8:45 am]
BILLING CODE 4910-13-P
