Airworthiness Directives; Boeing Model 747-100B SUD, 747-200B, 747-300, 747-400, and 747-400D Series Airplanes, 14367-14370 [06-2677]
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Federal Register / Vol. 71, No. 55 / Wednesday, March 22, 2006 / Rules and Regulations
14367
TABLE 1.—EMBRAER 170 AMM MAINTENANCE TASKS
AMM
chapter
Task Nos.
Date
Title
27–11–03 ....
27–41–01 ....
27–11–03–710–801–A, 27–11–03–720–801–A .......
27–41–01–210–801–A, 27–41–01–220–801–A, 27–
41–01–220–802–A.
27–81–01–710–801–A ..............................................
January 25, 2005 ....
January 25, 2005 ....
Aileron Control Cable–Adjustment/Test.
Horizontal Stabilizer Trim Actuator—Inspection/
Check.
Slat Actuator—Adjustment/Test.
27–81–01 ....
January 25, 2005 ....
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(g)(1) The Manager, ANM–116, Transport
Airplane Directorate, 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.
Federal Aviation Administration
Related Information
(h) Brazilian airworthiness directive 2005–
03–02, effective April 20, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
cprice-sewell on PROD1PC70 with RULES
(i) You must use EMBRAER Temporary
Revision 1–3 of the EMBRAER 170
Maintenance Review Board Report MRB–
1621, dated December 27, 2004, to the
EMBRAER 170 Airplane Maintenance
Manual, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Empresa Brasileira de Aeronautica
S.A. (EMBRAER), P.O. Box 343—CEP 12.225,
Sao Jose dos Campos—SP, Brazil, for a copy
of this service information. You may review
copies at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on March
10, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–2675 Filed 3–21–06; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2005–22383; Directorate
Identifier 2005–NM–102–AD; Amendment
39–14520; AD 2006–06–11]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100B SUD, 747–200B, 747–
300, 747–400, and 747–400D Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Boeing Model 747–100B SUD, 747–300,
747–400, and 747–400D series
airplanes; and Model 747–200B series
airplanes having a stretched upper deck.
This AD requires repetitively inspecting
for cracking or discrepancies of the
fasteners in the tension ties, shear webs,
and frames at body stations 1120
through 1220, and performing related
investigative and corrective actions if
necessary. This AD results from new
reports of severed tension ties, as well
as numerous reports of cracked tension
ties, broken fasteners, and cracks in the
frame, shear web, and shear ties
adjacent to tension ties for the upper
deck. We are issuing this AD to detect
and correct cracking of the tension ties,
shear webs, and frames of the upper
deck, which could result in rapid
decompression of the airplane.
DATES: This AD becomes effective April
26, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 26, 2006.
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,
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (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 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 would
apply to certain Boeing Model 747–
100B SUD, 747–300, 747–400, and 747–
400D series airplanes; and Model 747–
200B series airplanes having a stretched
upper deck (SUD). That NPRM was
published in the Federal Register on
September 12, 2005 (70 FR 53743). That
NPRM proposed to require repetitively
inspecting for cracking or discrepancies
of the fasteners in the tension ties, shear
webs, and frames at body stations 1120
through 1220, and related investigative
and corrective actions if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Discuss Special Freighters
The Boeing Company (hereafter
referred to in this AD as ‘‘Boeing’’)
requests that we revise the Discussion
section of the proposed AD to refer to
Boeing Model 747–200B(SUD)SF, 747–
300SF, and 747–400SF airplanes.
Boeing notes that the Discussion section
mentions Boeing 747–200B series
airplanes modified under a Boeing-
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Federal Register / Vol. 71, No. 55 / Wednesday, March 22, 2006 / Rules and Regulations
owned supplemental type certificate
(STC) to include a SUD, but doesn’t
mention STCs and service bulletins
related to converting airplanes into a
special freighter configuration. Boeing
requests that we add a paragraph to the
Discussion section stating that certain
‘‘Boeing Model 747–200B(SUD), 747–
300, and 747–400 series airplanes’’ have
been modified to a special freighter
configuration and are subject to the
identified unsafe condition for the
tension ties and frames at body stations
(BS) 1120 through 1220 only. Boeing
contends that tension ties and frames at
BS 880 through 1100 on the airplanes
configured as special freighters are more
robust and are not subject to the unsafe
condition. Boeing states that adding
such a paragraph would clarify that
special freighters are affected by the AD,
but that tension ties and frames at BS
880 through 1100 are not subject to the
AD.
We agree that a special freighter that
is converted from a Boeing 747–200B
series airplane having a SUD or from a
Boeing 747–300 or –400 series airplane
is subject to the unsafe condition
addressed by this AD. These airplanes
are already included in the applicability
of this AD. However, we do not agree
with Boeing’s request to refer to tension
ties and frames at BS 880 through 1100
on the airplanes converted to special
freighters because we have not indicated
that the tension ties and frames in this
area are subject to the AD. The
Discussion section of the proposed AD
is not restated in the final rule, so we
have made no change with regard to
Boeing’s request.
Request To Clarify Effect on Other ADs
Boeing also requests that we clarify
paragraph (b) of the proposed AD to
state that, for special freighters that are
converted from a Boeing 747–200B
series airplane having a SUD or from a
Boeing 747–300 or –400 series airplane,
the inspections in this AD will not
terminate the inspections of structural
significant item (SSI) F–19A of Boeing
Document No. D6–35022,
‘‘Supplemental Structural Inspection
Document (SSID),’’ Revision G, dated
December 2000 (hereafter referred to in
this AD as ‘‘the SSID’’) for BS 880
through 1100.
We agree that this AD does not
terminate the inspections of SSI F–19A
for BS 880 through 1100. As we stated
previously, tension ties and frames in
BS 880 through 1100 are not subject to
this AD. For clarification, we have
revised paragraph (b) of this AD to state
that the provisions of that paragraph
apply only to areas inspected in
accordance with this AD.
Request To Clarify Compliance Times
Boeing also requests that we revise
paragraph (f)(1) of the proposed AD to
state that the provision in that
paragraph applies only to airplanes
identified in Boeing Alert Service
Bulletin 747–53A2507. Boeing states
that, without this clarification, operators
may question whether paragraph (f)(1)
applies to all airplanes versus all
airplanes specified in Boeing Alert
Service Bulletin 747–53A2507.
We do not agree with Boeing’s request
to clarify the compliance times.
Paragraph (f) of this AD refers to
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2507 as
the source for compliance times,
‘‘except as provided by paragraphs
(f)(1), (f)(2), and (f)(3) of this AD.’’ The
compliance times in that service
bulletin are also summarized in the
preamble of the NPRM. We explained in
the preamble of the NPRM, under the
heading ‘‘Clarification of Compliance
Time for Stage 1 Inspections,’’ that this
AD applies to certain airplanes not
subject to the inspection in Boeing
Service Bulletin 747–53–2483.
Paragraph (f)(1) is intended to clarify the
applicable compliance time for the
Stage 1 inspections for these airplanes.
We find that no further clarification of
the compliance times is needed.
Request To Correct Typographical
Error
Boeing also requests that we revise
paragraph (c) of the proposed AD to
refer to Model 747–200B series
airplanes instead of ‘‘Model 747–200
series airplanes.’’ We agree. A
typographical error resulted in the
omission of the letter ‘‘B’’ from the
model. We have revised paragraph (c) of
this AD accordingly.
Clarification of Applicability
The proposed AD specified that the
actions therein would be applicable to
‘‘Boeing Model 747–100B SUD, 747–
300, 747–400, and 747–400D series
airplanes; and Model 747–200[B] series
airplanes having a stretched upper deck;
certificated in any category; as
identified in Boeing Alert Service
Bulletin 747–53A2507, dated April 21,
2005.’’ The current effectivity listing in
the service bulletin includes airplanes
up to and including line number 1358.
However, the service bulletin also
specifies that airplanes after line
number 1358 are affected. Therefore, for
clarification, we have revised this AD to
apply to all airplanes of the affected
models.
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 comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Interim Action
We consider this AD interim action.
The manufacturer is currently
developing a modification that will
address the unsafe condition identified
in this AD. Once this modification is
developed, approved, and available, we
may consider additional rulemaking.
Costs of Compliance
There are about 622 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.
ESTIMATED COSTS
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Action
Stage 1 Inspection per inspection cycle.1
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Average
labor rate
per hour
Work
hours
19
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$65
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Cost per
airplane
Number
of U.S.registered
airplanes
$1,235, per inspection cycle .....
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76
Fleet cost
$93,860, per inspection cycle.1
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Federal Register / Vol. 71, No. 55 / Wednesday, March 22, 2006 / Rules and Regulations
14369
ESTIMATED COSTS—Continued
Stage 2 Inspection, per inspection cycle.
1 Completing
Average
labor rate
per hour
Work
hours
Action
83
$5,395, per inspection cycle .....
76
Fleet cost
$410,020, per inspection cycle.
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.
15:10 Mar 21, 2006
Jkt 208001
Compliance
Adoption of the Amendment
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.
cprice-sewell on PROD1PC70 with RULES
Number
of U.S.registered
airplanes
the initial Stage 2 inspection ends the repetitive Stage 1 inspections.
Authority for This Rulemaking
VerDate Aug<31>2005
65
Cost per
airplane
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
(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.
Repetitive Inspections and Corrective
Actions
Applicability
(c) This AD applies to all Boeing Model
747–100B SUD, 747–300, 747–400, and 747–
400D series airplanes; and Model 747–200B
series airplanes having a stretched upper
deck; certificated in any category.
(f) Do repetitive detailed and high
frequency eddy current inspections, as
applicable, for cracking or discrepancies of
the fasteners in the tension ties, shear webs,
and frames at body stations 1120 through
1220, and related investigative and corrective
actions as applicable, by doing all actions in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2507, dated April 21, 2005, except
as provided by paragraphs (g) and (h) of this
AD. Do the initial and repetitive Stage 1 and
Stage 2 inspections at the applicable times
specified in Paragraph 1.E., ‘‘Compliance,’’ of
the service bulletin, except as provided by
paragraphs (f)(1), (f)(2), and (f)(3) of this AD.
Any applicable investigative and corrective
actions must be done before further flight.
Doing the initial Stage 2 inspection ends the
repetitive Stage 1 inspections.
(1) For any airplane not identified in and
subject to inspections in accordance with
Boeing Service Bulletin 747–53–2483: Do the
initial Stage 1 inspection in accordance with
Boeing Alert Service Bulletin 747–53A2507
before the accumulation of 8,000 total flight
cycles, or within 1,500 flight cycles after the
effective date of this AD, whichever is later.
(2) Where Paragraph 1.E., ‘‘Compliance,’’ of
the service bulletin specifies a compliance
time relative to the original issue date of the
service bulletin, this AD requires compliance
before the specified compliance time after the
effective date of this AD.
(3) For any airplane that reaches the
applicable compliance time for the initial
Stage 2 inspection (as specified in Table 1,
Compliance Recommendations, under
paragraph 1.E. of the service bulletin) before
reaching the applicable compliance time for
the initial Stage 1 inspection: Doing the
initial Stage 2 inspection eliminates the need
to do the Stage 1 inspection.
Unsafe Condition
(d) This AD results from new reports of
severed tension ties, as well as numerous
reports of cracked tension ties, broken
fasteners, and cracks in the frame, shear web,
and shear ties adjacent to tension ties for the
upper deck. We are issuing this AD to detect
and correct cracking of the tension ties, shear
webs, and frames of the upper deck, which
could result in rapid decompression of the
airplane.
Exception to Corrective Action Instructions
(g) If any discrepancy; including but not
limited to cracking, or broken, loose, or
missing fasteners; is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin 747–53A2507, dated
April 21, 2005, specifies to contact Boeing for
appropriate action: Before further flight,
repair the discrepancy using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–06–11 Boeing: Amendment 39–14520.
Docket No. FAA–2005–22383;
Directorate Identifier 2005–NM–102–AD.
Effective Date
(a) This AD becomes effective April 26,
2006.
Affected ADs
(b) For the areas inspected in accordance
with this AD, accomplishing the
requirements of paragraph (f) of this AD
terminates the corresponding inspection
requirements for the upper deck tension ties
as required by paragraphs (c) and (d) of AD
2004–07–22, amendment 39–13566, as those
paragraphs apply to inspections of structural
significant item (SSI) F–19A, as identified in
Boeing Document No. D6–35022,
‘‘Supplemental Structural Inspection
Document,’’ Revision G, dated December
2000. All other requirements of AD 2004–07–
22 continue to apply.
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Federal Register / Vol. 71, No. 55 / Wednesday, March 22, 2006 / Rules and Regulations
No Reporting Requirement
DEPARTMENT OF TRANSPORTATION
(h) Although Boeing Alert Service Bulletin
747–53A2507, dated April 21, 2005, specifies
reporting inspection findings to the
manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 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) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
(j) You must use Boeing Alert Service
Bulletin 747–53A2507, dated April 21, 2005,
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
The Director of the Federal Register approved
the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. 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 Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on March 9,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–2677 Filed 3–21–06; 8:45 am]
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BILLING CODE 4910–13–P
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15:10 Mar 21, 2006
Jkt 208001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22426; Directorate
Identifier 2005–NM–105–AD; Amendment
39–14519; AD 2006–06–10]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–300,
747–400, 747–400D, and 747SR Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Boeing Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–
300, 747–400, 747–400D, and 747SR
series airplanes. This AD requires a onetime inspection to determine whether
any steel doubler (small or large) is
installed at the lower forward and upper
aft corners of the fuselage cutout at main
entry doors (MEDs) number 3.
Depending on the results of this
inspection, this AD also requires
repetitive inspections for cracks of the
skin, bearstrap, and small steel doubler
(if installed) at the applicable corner or
corners of the fuselage cutouts, and
related investigative/corrective actions
if necessary. This AD also provides the
optional terminating action for the
repetitive inspections of installing a
large steel doubler at the affected
corners. This AD results from reports of
cracks in the skin and bearstrap at the
upper aft corner and at the lower
forward corner of the fuselage cutout at
MEDs number 3. We are issuing this AD
to detect and correct cracks in the skin,
bearstrap, and small steel doubler (if
installed), which could propagate and
result in rapid decompression of the
airplane.
This AD becomes effective April
26, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 26, 2006.
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,
DATES:
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (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 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 would
apply to all Boeing Model 747–100,
747–100B, 747–100B SUD, 747–200B,
747–200C, 747–300, 747–400, 747–
400D, and 747SR series airplanes. That
NPRM was published in the Federal
Register on September 16, 2005 (70 FR
54677). That NPRM proposed to require
a one-time inspection to determine
whether any steel doubler (small or
large) is installed at the lower forward
and upper aft corners of the fuselage
cutout at main entry doors (MEDs)
number 3. Depending on the results of
this inspection, that AD also proposed
to require repetitive inspections for
cracks of the skin, bearstrap, and small
steel doubler (if installed) at the
applicable corner or corners of the
fuselage cutouts, and related
investigative/corrective actions if
necessary. That AD also proposed the
optional terminating action for the
repetitive inspections of installing a
large steel doubler at the affected
corners.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Revise Paragraph (h) to
Include Reference to Small Steel
Doubler
Boeing requests that we revise
paragraph (h) ‘‘Inspection for Steel
Doublers’’ of the NPRM to include
instructions to inspect the small steel
doubler (if installed) for cracks. Boeing
points out that this inspection is
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]]>Agencies
[Federal Register Volume 71, Number 55 (Wednesday, March 22, 2006)]
[Rules and Regulations]
[Pages 14367-14370]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2677]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22383; Directorate Identifier 2005-NM-102-AD;
Amendment 39-14520; AD 2006-06-11]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100B SUD, 747-200B,
747-300, 747-400, and 747-400D Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Boeing Model 747-100B SUD, 747-300, 747-400, and 747-400D series
airplanes; and Model 747-200B series airplanes having a stretched upper
deck. This AD requires repetitively inspecting for cracking or
discrepancies of the fasteners in the tension ties, shear webs, and
frames at body stations 1120 through 1220, and performing related
investigative and corrective actions if necessary. This AD results from
new reports of severed tension ties, as well as numerous reports of
cracked tension ties, broken fasteners, and cracks in the frame, shear
web, and shear ties adjacent to tension ties for the upper deck. We are
issuing this AD to detect and correct cracking of the tension ties,
shear webs, and frames of the upper deck, which could result in rapid
decompression of the airplane.
DATES: This AD becomes effective April 26, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of April 26,
2006.
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: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (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 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 would apply to certain Boeing Model
747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and
Model 747-200B series airplanes having a stretched upper deck (SUD).
That NPRM was published in the Federal Register on September 12, 2005
(70 FR 53743). That NPRM proposed to require repetitively inspecting
for cracking or discrepancies of the fasteners in the tension ties,
shear webs, and frames at body stations 1120 through 1220, and related
investigative and corrective actions if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Discuss Special Freighters
The Boeing Company (hereafter referred to in this AD as ``Boeing'')
requests that we revise the Discussion section of the proposed AD to
refer to Boeing Model 747-200B(SUD)SF, 747-300SF, and 747-400SF
airplanes. Boeing notes that the Discussion section mentions Boeing
747-200B series airplanes modified under a Boeing-
[[Page 14368]]
owned supplemental type certificate (STC) to include a SUD, but doesn't
mention STCs and service bulletins related to converting airplanes into
a special freighter configuration. Boeing requests that we add a
paragraph to the Discussion section stating that certain ``Boeing Model
747-200B(SUD), 747-300, and 747-400 series airplanes'' have been
modified to a special freighter configuration and are subject to the
identified unsafe condition for the tension ties and frames at body
stations (BS) 1120 through 1220 only. Boeing contends that tension ties
and frames at BS 880 through 1100 on the airplanes configured as
special freighters are more robust and are not subject to the unsafe
condition. Boeing states that adding such a paragraph would clarify
that special freighters are affected by the AD, but that tension ties
and frames at BS 880 through 1100 are not subject to the AD.
We agree that a special freighter that is converted from a Boeing
747-200B series airplane having a SUD or from a Boeing 747-300 or -400
series airplane is subject to the unsafe condition addressed by this
AD. These airplanes are already included in the applicability of this
AD. However, we do not agree with Boeing's request to refer to tension
ties and frames at BS 880 through 1100 on the airplanes converted to
special freighters because we have not indicated that the tension ties
and frames in this area are subject to the AD. The Discussion section
of the proposed AD is not restated in the final rule, so we have made
no change with regard to Boeing's request.
Request To Clarify Effect on Other ADs
Boeing also requests that we clarify paragraph (b) of the proposed
AD to state that, for special freighters that are converted from a
Boeing 747-200B series airplane having a SUD or from a Boeing 747-300
or -400 series airplane, the inspections in this AD will not terminate
the inspections of structural significant item (SSI) F-19A of Boeing
Document No. D6-35022, ``Supplemental Structural Inspection Document
(SSID),'' Revision G, dated December 2000 (hereafter referred to in
this AD as ``the SSID'') for BS 880 through 1100.
We agree that this AD does not terminate the inspections of SSI F-
19A for BS 880 through 1100. As we stated previously, tension ties and
frames in BS 880 through 1100 are not subject to this AD. For
clarification, we have revised paragraph (b) of this AD to state that
the provisions of that paragraph apply only to areas inspected in
accordance with this AD.
Request To Clarify Compliance Times
Boeing also requests that we revise paragraph (f)(1) of the
proposed AD to state that the provision in that paragraph applies only
to airplanes identified in Boeing Alert Service Bulletin 747-53A2507.
Boeing states that, without this clarification, operators may question
whether paragraph (f)(1) applies to all airplanes versus all airplanes
specified in Boeing Alert Service Bulletin 747-53A2507.
We do not agree with Boeing's request to clarify the compliance
times. Paragraph (f) of this AD refers to paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2507 as the
source for compliance times, ``except as provided by paragraphs (f)(1),
(f)(2), and (f)(3) of this AD.'' The compliance times in that service
bulletin are also summarized in the preamble of the NPRM. We explained
in the preamble of the NPRM, under the heading ``Clarification of
Compliance Time for Stage 1 Inspections,'' that this AD applies to
certain airplanes not subject to the inspection in Boeing Service
Bulletin 747-53-2483. Paragraph (f)(1) is intended to clarify the
applicable compliance time for the Stage 1 inspections for these
airplanes. We find that no further clarification of the compliance
times is needed.
Request To Correct Typographical Error
Boeing also requests that we revise paragraph (c) of the proposed
AD to refer to Model 747-200B series airplanes instead of ``Model 747-
200 series airplanes.'' We agree. A typographical error resulted in the
omission of the letter ``B'' from the model. We have revised paragraph
(c) of this AD accordingly.
Clarification of Applicability
The proposed AD specified that the actions therein would be
applicable to ``Boeing Model 747-100B SUD, 747-300, 747-400, and 747-
400D series airplanes; and Model 747-200[B] series airplanes having a
stretched upper deck; certificated in any category; as identified in
Boeing Alert Service Bulletin 747-53A2507, dated April 21, 2005.'' The
current effectivity listing in the service bulletin includes airplanes
up to and including line number 1358. However, the service bulletin
also specifies that airplanes after line number 1358 are affected.
Therefore, for clarification, we have revised this AD to apply to all
airplanes of the affected models.
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
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Interim Action
We consider this AD interim action. The manufacturer is currently
developing a modification that will address the unsafe condition
identified in this AD. Once this modification is developed, approved,
and available, we may consider additional rulemaking.
Costs of Compliance
There are about 622 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.
Estimated Costs
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Number of
Average U.S.-
Action Work hours labor rate Cost per airplane registered Fleet cost
per hour airplanes
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Stage 1 Inspection per 19 $65 $1,235, per 76 $93,860, per
inspection cycle.\1\ inspection cycle. inspection
cycle.\1\
[[Page 14369]]
Stage 2 Inspection, per 83 65 $5,395, per 76 $410,020, per
inspection cycle. inspection cycle. inspection cycle.
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1 Completing the initial Stage 2 inspection ends the repetitive Stage 1 inspections.
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
adding the following new airworthiness directive (AD):
2006-06-11 Boeing: Amendment 39-14520. Docket No. FAA-2005-22383;
Directorate Identifier 2005-NM-102-AD.
Effective Date
(a) This AD becomes effective April 26, 2006.
Affected ADs
(b) For the areas inspected in accordance with this AD,
accomplishing the requirements of paragraph (f) of this AD
terminates the corresponding inspection requirements for the upper
deck tension ties as required by paragraphs (c) and (d) of AD 2004-
07-22, amendment 39-13566, as those paragraphs apply to inspections
of structural significant item (SSI) F-19A, as identified in Boeing
Document No. D6-35022, ``Supplemental Structural Inspection
Document,'' Revision G, dated December 2000. All other requirements
of AD 2004-07-22 continue to apply.
Applicability
(c) This AD applies to all Boeing Model 747-100B SUD, 747-300,
747-400, and 747-400D series airplanes; and Model 747-200B series
airplanes having a stretched upper deck; certificated in any
category.
Unsafe Condition
(d) This AD results from new reports of severed tension ties, as
well as numerous reports of cracked tension ties, broken fasteners,
and cracks in the frame, shear web, and shear ties adjacent to
tension ties for the upper deck. We are issuing this AD to detect
and correct cracking of the tension ties, shear webs, and frames of
the upper deck, which could result in rapid decompression of the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Repetitive Inspections and Corrective Actions
(f) Do repetitive detailed and high frequency eddy current
inspections, as applicable, for cracking or discrepancies of the
fasteners in the tension ties, shear webs, and frames at body
stations 1120 through 1220, and related investigative and corrective
actions as applicable, by doing all actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2507, dated April 21, 2005, except as provided by paragraphs (g)
and (h) of this AD. Do the initial and repetitive Stage 1 and Stage
2 inspections at the applicable times specified in Paragraph 1.E.,
``Compliance,'' of the service bulletin, except as provided by
paragraphs (f)(1), (f)(2), and (f)(3) of this AD. Any applicable
investigative and corrective actions must be done before further
flight. Doing the initial Stage 2 inspection ends the repetitive
Stage 1 inspections.
(1) For any airplane not identified in and subject to
inspections in accordance with Boeing Service Bulletin 747-53-2483:
Do the initial Stage 1 inspection in accordance with Boeing Alert
Service Bulletin 747-53A2507 before the accumulation of 8,000 total
flight cycles, or within 1,500 flight cycles after the effective
date of this AD, whichever is later.
(2) Where Paragraph 1.E., ``Compliance,'' of the service
bulletin specifies a compliance time relative to the original issue
date of the service bulletin, this AD requires compliance before the
specified compliance time after the effective date of this AD.
(3) For any airplane that reaches the applicable compliance time
for the initial Stage 2 inspection (as specified in Table 1,
Compliance Recommendations, under paragraph 1.E. of the service
bulletin) before reaching the applicable compliance time for the
initial Stage 1 inspection: Doing the initial Stage 2 inspection
eliminates the need to do the Stage 1 inspection.
Exception to Corrective Action Instructions
(g) If any discrepancy; including but not limited to cracking,
or broken, loose, or missing fasteners; is found during any
inspection required by this AD, and Boeing Alert Service Bulletin
747-53A2507, dated April 21, 2005, specifies to contact Boeing for
appropriate action: Before further flight, repair the discrepancy
using a method approved in accordance with the procedures specified
in paragraph (i) of this AD.
[[Page 14370]]
No Reporting Requirement
(h) Although Boeing Alert Service Bulletin 747-53A2507, dated
April 21, 2005, specifies reporting inspection findings to the
manufacturer, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
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) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
Material Incorporated by Reference
(j) You must use Boeing Alert Service Bulletin 747-53A2507,
dated April 21, 2005, to perform the actions that are required by
this AD, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
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 Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on March 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-2677 Filed 3-21-06; 8:45 am]
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