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, 31984-31988 [E7-10982]
Download as PDF
<![CDATA[
31984
Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Rules and Regulations
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: The MCAI
does not indicate that doing the actions
specified in Dassault Service Bulletin F50–
456, dated October 25, 2006, terminates the
requirement to disable the coffee-maker. This
AD indicates that doing the actions specified
in Dassault Service Bulletin F50–456
terminates the requirements to disable the
coffee-maker, and after the actions have been
done, the circuit breaker collar may be
removed.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Rodriguez,
Aerospace Engineer, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356, telephone
(425) 227–1137; fax (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Emergency Airworthiness
Directive 2006–0329–E, dated October 25,
2006; Dassault Service Bulletin F50–471,
dated October 25, 2006; and Dassault Service
Bulletin F50–456, dated October 25, 2006; for
related information.
Material Incorporated by Reference
(i) You must use the service information
specified in Table 1 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey 07606.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Dassault Service Bulletin
Revision level
F50–456 ......................................................................................................................................................
F50–471 ......................................................................................................................................................
Original .............
Original .............
Issued in Renton, Washington, on May 30,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10991 Filed 6–8–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27525; Directorate
Identifier 2006–NM–159–AD; Amendment
39–15089; AD 2007–12–11]
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: Final rule.
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AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747 airplanes. That AD currently
requires repetitive inspections to detect
cracks and/or corrosion of the girt bar
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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 new AD requires 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 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
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.
This AD becomes effective July
16, 2007.
DATES:
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Date
October 25, 2006.
October 25, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of July 16, 2007.
On December 16, 1996 (61 FR 58318,
November 14, 1996), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Service Bulletin 747–53A2378, Revision
1, dated March 10, 1994.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
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:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
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Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Rules and Regulations
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 96–23–05, amendment
39–9810 (61 FR 58318, November 14,
1996). The existing AD applies to
certain Boeing Model 747 airplanes.
That NPRM was published in the
Federal Register on March 15, 2007 (72
FR 12136). That NPRM proposed to
continue to require 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. The NPRM also
proposed to 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.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the single comment that has
been received on the NPRM. The
commenter, Boeing, supports the
NPRM.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
31985
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Conclusion
We have carefully reviewed the
available data, including the comment
that has been received, and determined
that air safety and the public interest
require adopting the AD with the
change described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
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 AD. The average labor
rate per work hour is $80. The cost
varies depending on the configuration of
the airplane.
ESTIMATED COSTS
Work hours
Cost per airplane
Number of
U.S.-registered
airplanes
Inspection of MEDs (required
by AD 96–23–05).
Between 88 and 102 .............
Between $7,040 and $8,160,
per inspection cycle.
169 ..................
Inspection for correct installation (new required action).
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Action
6 .............................................
$480 .......................................
Up to 169 ........
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.
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
List of Subjects in 14 CFR Part 39
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Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Fleet cost
Between $1,189,760 and
$1,379,040, per inspection
cycle.
Up to $81,120.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 by
adding the following new airworthiness
directive (AD):
■
2007–12–11 Boeing: Amendment 39–15089.
Docket No. FAA–2007–27525;
Directorate Identifier 2006–NM–159–AD.
Effective Date
(a) This AD becomes effective July 16,
2007.
Affected ADs
(b) This AD supersedes AD 96–23–05.
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Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Rules and Regulations
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
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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,
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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
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
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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 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–
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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
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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
(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.
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.
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
Alternative Methods of Compliance (AMOCs)
(w)(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.
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
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 in 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 in 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 Boeing Service Bulletin 747–
53A2378, Revision 3, dated August 11, 2005,
specifies contacting Boeing for appropriate
action: Before further flight, do the repair
using a method approved by the Manager,
Seattle ACO, 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.
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Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Rules and Regulations
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in
accordance with AD 96–23–05, are approved
as AMOCs for the corresponding provisions
of this AD.
Material Incorporated by Reference
(x) You must use Boeing Service Bulletin
747–53A2378, Revision 1, dated March 10,
1994; or Boeing Service Bulletin 747–
53A2378, Revision 3, dated August 11, 2005;
as applicable, to perform the actions that are
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Service Bulletin 747–53A2378,
Revision 3, dated August 11, 2005, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On December 16, 1996 (61 FR 58318,
November 14, 1996), the Director of the
Federal Register approved the incorporation
by reference of Boeing Service Bulletin 747–
53A2378, Revision 1, dated March 10, 1994.
(3) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, for a copy of this service information.
You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on May 30,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10982 Filed 6–8–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27071; Directorate
Identifier 2007–CE–004–AD; Amendment
39–15084; AD 2007–12–06]
RIN 2120–AA64
Airworthiness Directives; Hawker
Beechcraft Corporation (Type
Certificate (TC) No. 3A20 and TC No.
A24CE Formerly Held by Raytheon
Aircraft Corporation and Beech)
Models C90A, B200, B200C, B300, and
B300C Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) that
supersedes AD 2006–23–02, which
applies to certain Hawker Beechcraft
Corporation (HBC) (Type Certificate
(TC) No. 3A20 and TC No. A24CE
formerly held by Raytheon Aircraft
Corporation and Beech) Models C90A,
B200, B200C, B300, and B300C
airplanes. AD 2006–23–02 currently
requires you to inspect the flight
controls for improper assembly or
damage, and if any improperly
assembled or damaged flight controls
are found, take corrective action. Since
we issued AD 2006–23–02, we have
determined the need to add airplane
serial numbers that were not previously
included in the applicability.
Consequently, this AD retains the
actions of AD 2006–23–02 and adds
airplane serial numbers to the
applicability. We are issuing this AD to
detect and correct improperly
assembled or damaged flight controls,
which could result in an unsafe
condition by reducing capabilities of the
flight controls and lead to loss of
control.
SUMMARY:
This AD becomes effective on
July 16, 2007.
On July 16, 2007, the Director of the
Federal Register approved the
incorporation by reference of Raytheon
Aircraft Company Mandatory Service
Bulletin Number SB 27–3761, Rev. 1,
December 2006, listed in this AD.
As of December 13, 2006 (71 FR
65390 Nov. 8, 2006), the Director of the
Federal Register approved the
incorporation by reference of Raytheon
Aircraft Company Mandatory Service
Bulletin Number SB 27–3761, Issued:
February 2006, listed in this AD.
rmajette on DSK8KYBLC1PROD with MISCELLANEOUS
DATES:
VerDate Mar<15>2010
12:20 Mar 07, 2011
Jkt 223001
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
For service information
identified in this AD, contact Hawker
Beechcraft Corporation, P.O. Box 85,
Wichita, Kansas 67201–0085; telephone:
(800) 429–5372 or (316) 676–3140.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2007–27071; Directorate Identifier
2007–CE–004–AD.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Chris B. Morgan, Aerospace Engineer,
FAA, Wichita Aircraft Certification
Office, 1801 Airport Road, Wichita,
Kansas 67209; telephone: (316) 946–
4154; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
On March 6, 2007, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain HBC Models C90A, B200,
B200C, B300, and B300C airplanes. This
proposal was published in the Federal
Register as a notice of proposed
rulemaking (NPRM) on March 12, 2007
(72 FR 10949). The NPRM proposed to
retain the actions of AD 2006–23–02
and add airplane serial numbers to the
applicability.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 138
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection:
E:\ERIC\11JNR1.SGM
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]]>Agencies
[Federal Register Volume 72, Number 111 (Monday, June 11, 2007)]
[Rules and Regulations]
[Pages 31984-31988]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10982]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27525; Directorate Identifier 2006-NM-159-AD;
Amendment 39-15089; AD 2007-12-11]
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: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747 airplanes. That 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 new AD requires 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 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 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.
DATES: This AD becomes effective July 16, 2007.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of July 16,
2007.
On December 16, 1996 (61 FR 58318, November 14, 1996), the Director
of the Federal Register approved the incorporation by reference of
Boeing Service Bulletin 747-53A2378, Revision 1, dated March 10, 1994.
ADDRESSES: You may examine the AD docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: 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:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the
[[Page 31985]]
Docket Management Facility office between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays. The Docket Management Facility
office (telephone (800) 647-5227) is located on the plaza level of the
Nassif Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 96-23-05, amendment 39-
9810 (61 FR 58318, November 14, 1996). The existing AD applies to
certain Boeing Model 747 airplanes. That NPRM was published in the
Federal Register on March 15, 2007 (72 FR 12136). That NPRM proposed to
continue to require 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. The NPRM also proposed to 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.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the single comment that has
been received on the NPRM. The commenter, Boeing, supports the NPRM.
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.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
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 AD. The average labor rate per work
hour is $80. The cost varies depending on the configuration of the
airplane.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Cost per airplane registered airplanes Fleet cost
----------------------------------------------------------------------------------------------------------------
Inspection of MEDs (required by Between 88 and 102 Between $7,040 and 169................. Between
AD 96-23-05). $8,160, per $1,189,760 and
inspection cycle. $1,379,040, per
inspection
cycle.
Inspection for correct 6................. $480.............. Up to 169........... Up to $81,120.
installation (new required
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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-9810 (61 FR 58318, November 14, 1996) and by
adding the following new airworthiness directive (AD):
2007-12-11 Boeing: Amendment 39-15089. Docket No. FAA-2007-27525;
Directorate Identifier 2006-NM-159-AD.
Effective Date
(a) This AD becomes effective July 16, 2007.
Affected ADs
(b) This AD supersedes AD 96-23-05.
[[Page 31986]]
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 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-
[[Page 31987]]
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
(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 in 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 in 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 Boeing Service Bulletin 747-
53A2378, Revision 3, dated August 11, 2005, specifies contacting
Boeing for appropriate action: Before further flight, do the repair
using a method approved by the Manager, Seattle ACO, 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, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
[[Page 31988]]
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) AMOCs approved previously in accordance with AD 96-23-05,
are approved as AMOCs for the corresponding provisions of this AD.
Material Incorporated by Reference
(x) You must use Boeing Service Bulletin 747-53A2378, Revision
1, dated March 10, 1994; or Boeing Service Bulletin 747-53A2378,
Revision 3, dated August 11, 2005; as applicable, to perform the
actions that are required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Service Bulletin 747-53A2378,
Revision 3, dated August 11, 2005, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On December 16, 1996 (61 FR 58318, November 14, 1996), the
Director of the Federal Register approved the incorporation by
reference of Boeing Service Bulletin 747-53A2378, Revision 1, dated
March 10, 1994.
(3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on May 30, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10982 Filed 6-8-07; 8:45 am]
BILLING CODE 4910-13-P
