Airworthiness Directives; Boeing Model 747 Airplanes, 56861-56864 [06-8227]
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Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations
56861
TABLE 1.—CREDIT SERVICE BULLETINS
BAE Systems (Operations) Limited Inspection
Service Bulletin
Revision level
ISB.53–005 ...........................................................................
ISB.53–067 ...........................................................................
Revision 1 ............................................................................
Revision 1 ............................................................................
Revision 2 ............................................................................
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(k)(1) The Manager, International Branch,
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
(l) British airworthiness directive G–2005–
0020, dated July 6, 2005, also addresses the
subject of this AD.
Material Incorporated by Reference
(m) You must use BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.53–005, Revision 2, dated
February 16, 2004; and BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.53–067, Revision 3, dated June
27, 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 these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact British Aerospace Regional Aircraft
American Support, 13850 Mclearen Road,
Herndon, Virginia 20171, 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
September 15, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–8231 Filed 9–27–06; 8:45 am]
jlentini on PROD1PC65 with RULES
BILLING CODE 4910–13–P
17:21 Sep 27, 2006
[Docket No. FAA–2006–24865; Directorate
Identifier 2005–NM–194–AD; Amendment
39–14771; AD 2006–20–02]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
Related Information
VerDate Aug<31>2005
14 CFR Part 39
Jkt 208001
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747 airplanes. That AD currently
requires inspections to detect
disbonding, corrosion, and cracking at
the longitudinal rows of fasteners in the
bonded skin panels in section 41 of the
fuselage, and repair, if necessary. This
new AD adds airplanes to the
applicability, and requires new
inspections of airplanes that may have
Alodine-coated rivets installed. This AD
results from a report of cracking
discovered in a skin lap joint that was
previously inspected using the eddy
current method. We are issuing this AD
to prevent rapid decompression of the
airplane due to disbonding and
subsequent cracking of the skin panels.
DATES: This AD becomes effective
November 2, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 2, 2006.
On November 27, 1996 (61 FR 57994,
November 12, 1996), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 747–53A2409,
dated September 26, 1996.
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,
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Date
April 19, 1985.
February 16, 1990.
February 16, 2004.
Washington 98124–2207, for service
information identified in this AD.
Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6437;
fax (425) 917–6590.
FOR FURTHER INFORMATION CONTACT:
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
supersedes AD 96–23–02, amendment
39–9807 (61 FR 57994, November 12,
1996). The existing AD applies to
certain Boeing Model 747 series
airplanes. That NPRM was published in
the Federal Register on May 25, 2006
(71 FR 30090). That NPRM proposed to
continue to require inspections to detect
disbonding, corrosion, and cracking at
the longitudinal rows of fasteners in the
bonded skin panels in section 41 of the
fuselage, and repair, if necessary. That
NPRM also proposed to add airplanes to
the applicability of the existing AD, and
require new inspections of airplanes
that may have Alodine-coated rivets
installed.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Support for the NPRM
Boeing supports the NPRM.
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56862
Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations
Request To Clarify Inspection
Applicability in Paragraph (g)(1) of the
NPRM
Northwest Airlines (NWA) requests
that we use ‘‘and/or’’ in place of ‘‘and’’
in paragraph (g)(1) of the NPRM, as
follows: ‘‘* * * do initial inspections of
Area 4 and repetitive inspections, as
applicable, to detect disbonding,
corrosion, and/or cracking of the skin;
* * *.’’ NWA explains that changing
‘‘and’’ to ‘‘and/or’’ provides clear
instruction for accomplishing the
inspection of Area 4 using one of the
inspection methods defined in Figure 18
or 20 of Boeing Alert Service Bulletin
747–53A2409, Revision 5, dated August
18, 2005, which was referenced in the
NPRM as the appropriate source of
service information for accomplishing
the required actions. NWA states that
the requested change eliminates all
possibility of interpreting the NPRM to
require a specific inspection for
disbonding, corrosion, and cracking
using the applicable method for each
inspection as defined in the service
bulletin. NWA also states that this
change would duplicate the inspection
methods specified in paragraphs (b), (h),
and (n) of AD 96–23–02, which used the
words ‘‘and/or’’ in a similar context.
This change would ensure the NPRM
provides clear definition that an
operator would accomplish one
inspection using the applicable method
to detect disbonding, corrosion, or
cracks, rather than accomplishing three
inspections for three specific and
separate conditions.
We agree that the paragraph should be
clarified to provide clear instruction for
accomplishing the inspection of Area 4
using one of the inspection methods
defined in the service bulletin. We
disagree with using the words ‘‘and/or.’’
Our recent policy has been to avoid
using and/or, which can often be subject
to misinterpretation. Therefore, we have
changed paragraph (g)(1) of this AD by
adding ‘‘as applicable’’ at the end of the
phrase as follows: ‘‘* * * do initial
inspections of Area 4 and repetitive
inspections, as applicable, to detect
disbonding, corrosion, and cracking of
the skin, as applicable; * * * .’’
Request To Clarify Inspection Methods
in Paragraph (g)(1) of the NPRM
NWA also requests that we change the
inspection methods in paragraph (g)(1)
of the NPRM from ‘‘Method 1 or 2’’ to
‘‘Method 2, 3, or 4’’ as follows: ‘‘If
inspection Method 2, 3, or 4 is used and
no disbonded doubler is found, no
further action is required by this AD.’’
NWA explains that changing the
inspection methods from ‘‘Method 1 or
2’’ to ‘‘Method 2, 3, or 4’’ would define
the inspection methods necessary to
inspect the fuselage skins. Inspection
Method 1 is an external ultrasonic
inspection that is not applicable to Area
4. Inspection Methods 2, 3, and 4 are
inspections that apply to Area 4 and are
defined in Figure 20 of the service
bulletin.
We partially agree. We agree that
inspection Method 1 does not belong in
the paragraph because the Method 1
inspection is applicable only to areas 1,
2, and 3. We disagree with including
Methods 3 and 4 in a statement that
contains the words, ‘‘no further action is
required by this AD.’’ Inspection
Methods 3 and 4 are repetitive
inspections. If we included these
inspection methods in this statement,
then the repetitive inspections would no
longer be required. Therefore, we have
changed the specified part of paragraph
(g)(1) of the final rule as follows: ‘‘If
inspection Method 2 is used and no
disbonded doubler is found, no further
action is required by this AD.’’
Furthermore, we eliminated all other
references to Method 1 from the
paragraph.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been 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.
Costs of Compliance
There are about 623 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 is $80 per work hour.
ESTIMATED COSTS
Action
Work hours
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Inspections (required by AD 96–23–02, and continued in this AD) ........
New inspections (for airplanes with Alodine-coated rivets) .....................
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
VerDate Aug<31>2005
17:21 Sep 27, 2006
Jkt 208001
Cost per
airplane, per
inspection
cycle
308
42
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
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U.S.-registered
airplanes
$24,640
3,360
79
96
Fleet cost, per
inspection cycle
$1,946,560.
Up to $322,560.
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.
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Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
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 removing amendment 39–9807 (61
FR 57994, November 12, 1996) and by
adding the following new airworthiness
directive (AD):
I
2006–20–02 Boeing: Amendment 39–14771.
Docket No. FAA–2006–24865;
Directorate Identifier 2005–NM–194–AD.
Effective Date
(a) This AD becomes effective November 2,
2006.
Affected ADs
(b) This AD supersedes AD 96–23–02.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747–400,
747–400D, 747–400F, 747SR, and 747SP
series airplanes, certificated in any category;
as identified in Boeing Alert Service Bulletin
747–53A2409, Revision 5, dated August 18,
2005.
Unsafe Condition
(d) This AD results from a report of
cracking discovered in a skin lap joint that
was previously inspected using the eddy
current method. We are issuing this AD to
prevent rapid decompression of the airplane
due to disbonding and subsequent cracking
of the skin panels.
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.
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Requirements of AD 96–23–02
Actions for Groups 1 Through 10, and 17
Through 36, as Specified in Boeing Alert
Service Bulletin 747–53A2409, Revision 5
(f) For airplanes identified as Groups 1
through 10 inclusive, and 17 through 36
inclusive, in Boeing Alert Service Bulletin
747–53A2409, Revision 5, dated August 18,
2005: Do the inspections in paragraph (f)(1)
VerDate Aug<31>2005
17:21 Sep 27, 2006
Jkt 208001
of this AD; and do the corrective action in
paragraph (f)(2) of this AD as applicable.
Except as provided by paragraph (i) of this
AD, do all actions in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2409, dated
September 26, 1996; or Revision 5, dated
August 18, 2005. After the effective date of
this AD, only Revision 5 of the service
bulletin may be used.
(1) At the applicable time in Figures 1, 2,
18, and 20 of Revision 5 of the service
bulletin, do initial and repetitive inspections
of Areas 1 and 4, as applicable, to detect
disbonding, corrosion, and cracking of the
skin; except any inspection using Method 1
or 2 must not be accomplished before the
latest of the following, as applicable: Before
the accumulation of 2,000 total flight cycles;
2,000 flight cycles since modification to the
stretched upper deck (SUD) configuration; or
2,000 flight cycles since skin panel
replacement in accordance with AD 90–26–
10, amendment 39–6836. If inspection
Method 1 or 2 is used and no disbonded
doubler is found, no further action is
required by this AD.
(2) If any corrosion or cracking is found
during any inspection required by paragraph
(f)(1) of this AD: Before further flight, except
as provided by paragraph (i) of this AD,
repair and do any applicable related
investigative actions in accordance with the
Accomplishment Instructions of Revision 5
of the service bulletin.
New Requirements of This AD
Actions for Groups 11 Through 16 as
Specified in Boeing Alert Service Bulletin
747–53A2409, Revision 5 (Airplanes Added
to the Applicability of This AD)
(g) For airplanes identified as Groups 11
through 16 inclusive in Boeing Alert Service
Bulletin 747–53A2409, Revision 5, dated
August 18, 2005: Do the inspections in
paragraph (g)(1) of this AD; and do the
corrective action in paragraph (g)(2) of this
AD as applicable. Except as provided by
paragraph (i) of this AD, do all actions in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2409, Revision 5, dated August 18,
2005.
(1) At the applicable time in Figures 18 and
20 of the service bulletin, do initial
inspections of Area 4 and repetitive
inspections, as applicable, to detect
disbonding, corrosion, and cracking of the
skin, as applicable; except any inspection
using Method 2 must not be accomplished
before the latest of the following, as
applicable: Before the accumulation of 2,000
total flight cycles; 2,000 flight cycles since
modification to the SUD configuration; or
2,000 flight cycles since skin panel
replacement in accordance with AD 90–26–
10. If inspection Method 2 is used and no
disbonded doubler is found, no further action
is required by this AD.
(2) If any corrosion, disbonding, or
cracking is found during any inspection
required by paragraph (g)(1) of this AD,
before further flight: Repair and do any
applicable related investigative actions in
accordance with the Accomplishment
Instructions of the service bulletin.
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56863
Actions for Airplanes With Alodine-Coated
Rivets for Groups 1 Through 10, and 17
Through 36 as Specified in Boeing Alert
Service Bulletin 747–53A2409, Revision 5
(h) For airplanes identified as Groups 1
through 10 inclusive, and 17 through 36
inclusive, in Boeing Alert Service Bulletin
747–53A2409, Revision 5, dated August 18,
2005: Do the inspections in paragraph (h)(1)
of this AD; and do the corrective action in
paragraph (h)(2) of this AD if necessary.
Except as provided by paragraph (i) of this
AD, do all actions in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2409, Revision 5,
dated August 18, 2005.
(1) At the applicable time in Figures 21 and
22 of the service bulletin: Do initial and
repetitive inspections of Areas 1 and 4, as
applicable, to detect cracking of the skin.
(2) If any cracking is found during any
inspection required by paragraph (h)(1) of
this AD, before further flight: Repair in
accordance with the Accomplishment
Instructions of the service bulletin.
Exceptions
(i) Do all actions in accordance with the
applicable service bulletin except as
provided by paragraphs (i)(1), (i)(2), (i)(3),
(i)(4), and (i)(5) of this AD.
(1) For the action in paragraph (f)(1) of this
AD: Where Boeing Alert Service Bulletin
747–53A2409, dated September 26, 1996;
and Boeing Alert Service Bulletin 747–
53A2409, Revision 5, dated August 18, 2005;
specify a compliance time after the issuance
of any revision of the service bulletin, this
paragraph requires compliance before the
specified compliance time after November
27, 1996 (the effective date of AD 96–23–02).
(2) For the actions in paragraphs (g)(1) and
(h)(1) of this AD: Where Boeing Alert Service
Bulletin 747–53A2409, Revision 5, dated
August 18, 2005, specifies a compliance time
after the issuance or receipt of any revision
of the service bulletin, this paragraph
requires compliance before the specified
compliance time after the effective date of
this AD.
(3) For any repair or any inspection where
Boeing Alert Service Bulletin 747–53A2409,
Revision 5, dated August 18, 2005, specifies
to contact the manufacturer for further
instructions: Before further flight, repair or
inspect using a method approved in
accordance with the procedures specified in
paragraph (k) of this AD.
(4) If corrosion is found during any
inspection required by this AD, before further
flight: Repair in accordance with an FAAapproved method.
(5) Where Boeing Alert Service Bulletin
747–53A2409, Revision 5, dated August 18,
2005, specifies that it is not necessary to
count flight cycles at 2.0 psi or less cabin
differential pressure, this AD does not allow
for that adjustment factor.
Credit for Actions Accomplished Previously
(j) Actions done before the effective date of
this AD in accordance with the service
bulletins specified in Table 1 of this AD are
acceptable for compliance with the
corresponding requirements of paragraphs (f)
and (g) of this AD.
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56864
Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations
TABLE 1.—CREDIT SERVICE BULLETINS
Revision
level
Service bulletin
Boeing
Boeing
Boeing
Boeing
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
747–53A2409
747–53A2409
747–53A2409
747–53A2409
....................................................................................................................
....................................................................................................................
....................................................................................................................
....................................................................................................................
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Alternative Methods of Compliance (AMOCs)
(k)(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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 96–23–02, are approved
as AMOCs for the corresponding provisions
of paragraph (f) of this AD, except AMOCs for
terminating action based upon inspection
results using a sliding probe low frequency
eddy current (LFEC), sliding probe high
frequency eddy current (HFEC), or mid
frequency surface eddy current (MFEC)
inspection methods; and provided that any
alternative method for future inspections did
not incorporate a sliding probe LFEC, sliding
probe HFEC, or MFEC inspection methods.
(4) 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
(l) You must use Boeing Alert Service
Bulletin 747–53A2409, dated September 26,
1996; or Boeing Alert Service Bulletin 747–
53A2409, Revision 5, dated August 18, 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 Alert Service Bulletin 747–53A2409,
Revision 5, dated August 18, 2005, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On November 27, 1996 (61 FR 57994,
November 12, 1996), the Director of the
Federal Register approved the incorporation
by reference of Boeing Alert Service Bulletin
747–53A2409, dated September 26, 1996.
(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 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
VerDate Aug<31>2005
17:21 Sep 27, 2006
Jkt 208001
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
September 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–8227 Filed 9–27–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–23392; Directorate
Identifier 2005–NE–47–AD; Amendment 39–
14776; AD 2006–20–07]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation Models 250–C30, 250–C40,
and 250–C47 Series Turboshaft
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for RollsRoyce Corporation (RRC) models 250–
C30, 250–40, and 250–C47 series
turboshaft engines with a third-stage
turbine wheel, part number (P/N)
6898663 or P/N 23065843 installed, or
a fourth-stage turbine wheel, P/N
6892764 or P/N 23066744, installed.
This AD adds an additional life limit for
third- and fourth-stage turbine wheels.
This AD results from analysis by RRC of
failures of third-stage turbine wheels.
We are issuing this AD to prevent loss
of power, possible engine shutdown, or
uncontained engine failure.
DATES: This AD becomes effective
November 2, 2006. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of November 2, 2006.
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1
2
3
4
Date
May 29, 1997.
August 6, 1998.
October 22, 1998.
February 17, 2000.
You can get the service
information identified in this AD from
Rolls-Royce Corporation, P.O. Box 420,
Indianapolis, IN 46206–0420; telephone
(317) 230–6400; fax (317) 230–4243.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: John
Tallarovic, Aerospace Engineer, Chicago
Aircraft Certification Office, FAA, 2300
East Devon Avenue, Des Plaines, IL
60018–4696; telephone (847) 294–8180;
fax (847) 294–7834.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to RRC models 250–C30, 250–
40, and 250–C47 series turboshaft
engines. We published the proposed AD
in the Federal Register on January 25,
2006 (71 FR 4065). That action proposed
to add an additional life limit for thirdand fourth-stage turbine wheels.
ADDRESSES:
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility Docket Office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Office (telephone (800) 647–5227) is
located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request to Correct Factual Errors
One commenter, RRC, requests that
we correct factual errors in the NPRM
and revise the Discussion paragraph, to
state that:
• Only third-stage turbine wheels
actually failed in the past; and
• Only the third-stage turbine wheel
(not the third-and-fourth-stage turbine
E:\FR\FM\28SER1.SGM
28SER1
]]>Agencies
[Federal Register Volume 71, Number 188 (Thursday, September 28, 2006)]
[Rules and Regulations]
[Pages 56861-56864]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-8227]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24865; Directorate Identifier 2005-NM-194-AD;
Amendment 39-14771; AD 2006-20-02]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 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 inspections to detect disbonding, corrosion, and
cracking at the longitudinal rows of fasteners in the bonded skin
panels in section 41 of the fuselage, and repair, if necessary. This
new AD adds airplanes to the applicability, and requires new
inspections of airplanes that may have Alodine-coated rivets installed.
This AD results from a report of cracking discovered in a skin lap
joint that was previously inspected using the eddy current method. We
are issuing this AD to prevent rapid decompression of the airplane due
to disbonding and subsequent cracking of the skin panels.
DATES: This AD becomes effective November 2, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 2,
2006.
On November 27, 1996 (61 FR 57994, November 12, 1996), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 747-53A2409, dated September 26, 1996.
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 98057-3356; 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 supersedes AD 96-23-02, amendment 39-
9807 (61 FR 57994, November 12, 1996). The existing AD applies to
certain Boeing Model 747 series airplanes. That NPRM was published in
the Federal Register on May 25, 2006 (71 FR 30090). That NPRM proposed
to continue to require inspections to detect disbonding, corrosion, and
cracking at the longitudinal rows of fasteners in the bonded skin
panels in section 41 of the fuselage, and repair, if necessary. That
NPRM also proposed to add airplanes to the applicability of the
existing AD, and require new inspections of airplanes that may have
Alodine-coated rivets installed.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Support for the NPRM
Boeing supports the NPRM.
[[Page 56862]]
Request To Clarify Inspection Applicability in Paragraph (g)(1) of the
NPRM
Northwest Airlines (NWA) requests that we use ``and/or'' in place
of ``and'' in paragraph (g)(1) of the NPRM, as follows: ``* * * do
initial inspections of Area 4 and repetitive inspections, as
applicable, to detect disbonding, corrosion, and/or cracking of the
skin; * * *.'' NWA explains that changing ``and'' to ``and/or''
provides clear instruction for accomplishing the inspection of Area 4
using one of the inspection methods defined in Figure 18 or 20 of
Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18,
2005, which was referenced in the NPRM as the appropriate source of
service information for accomplishing the required actions. NWA states
that the requested change eliminates all possibility of interpreting
the NPRM to require a specific inspection for disbonding, corrosion,
and cracking using the applicable method for each inspection as defined
in the service bulletin. NWA also states that this change would
duplicate the inspection methods specified in paragraphs (b), (h), and
(n) of AD 96-23-02, which used the words ``and/or'' in a similar
context. This change would ensure the NPRM provides clear definition
that an operator would accomplish one inspection using the applicable
method to detect disbonding, corrosion, or cracks, rather than
accomplishing three inspections for three specific and separate
conditions.
We agree that the paragraph should be clarified to provide clear
instruction for accomplishing the inspection of Area 4 using one of the
inspection methods defined in the service bulletin. We disagree with
using the words ``and/or.'' Our recent policy has been to avoid using
and/or, which can often be subject to misinterpretation. Therefore, we
have changed paragraph (g)(1) of this AD by adding ``as applicable'' at
the end of the phrase as follows: ``* * * do initial inspections of
Area 4 and repetitive inspections, as applicable, to detect disbonding,
corrosion, and cracking of the skin, as applicable; * * * .''
Request To Clarify Inspection Methods in Paragraph (g)(1) of the NPRM
NWA also requests that we change the inspection methods in
paragraph (g)(1) of the NPRM from ``Method 1 or 2'' to ``Method 2, 3,
or 4'' as follows: ``If inspection Method 2, 3, or 4 is used and no
disbonded doubler is found, no further action is required by this AD.''
NWA explains that changing the inspection methods from ``Method 1 or
2'' to ``Method 2, 3, or 4'' would define the inspection methods
necessary to inspect the fuselage skins. Inspection Method 1 is an
external ultrasonic inspection that is not applicable to Area 4.
Inspection Methods 2, 3, and 4 are inspections that apply to Area 4 and
are defined in Figure 20 of the service bulletin.
We partially agree. We agree that inspection Method 1 does not
belong in the paragraph because the Method 1 inspection is applicable
only to areas 1, 2, and 3. We disagree with including Methods 3 and 4
in a statement that contains the words, ``no further action is required
by this AD.'' Inspection Methods 3 and 4 are repetitive inspections. If
we included these inspection methods in this statement, then the
repetitive inspections would no longer be required. Therefore, we have
changed the specified part of paragraph (g)(1) of the final rule as
follows: ``If inspection Method 2 is used and no disbonded doubler is
found, no further action is required by this AD.'' Furthermore, we
eliminated all other references to Method 1 from the paragraph.
Conclusion
We have carefully reviewed the available data, including the
comments that have been 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.
Costs of Compliance
There are about 623 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 is $80
per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
airplane, per U.S.- Fleet cost, per inspection
Action Work hours inspection registered cycle
cycle airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 96-23- 308 $24,640 79 $1,946,560.
02, and continued in this AD).
New inspections (for airplanes 42 3,360 96 Up to $322,560.
with Alodine-coated rivets).
----------------------------------------------------------------------------------------------------------------
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.
[[Page 56863]]
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 39-9807 (61 FR 57994, November 12, 1996) and by
adding the following new airworthiness directive (AD):
2006-20-02 Boeing: Amendment 39-14771. Docket No. FAA-2006-24865;
Directorate Identifier 2005-NM-194-AD.
Effective Date
(a) This AD becomes effective November 2, 2006.
Affected ADs
(b) This AD supersedes AD 96-23-02.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SR, and 747SP series airplanes, certificated in any
category; as identified in Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005.
Unsafe Condition
(d) This AD results from a report of cracking discovered in a
skin lap joint that was previously inspected using the eddy current
method. We are issuing this AD to prevent rapid decompression of the
airplane due to disbonding and subsequent cracking of the skin
panels.
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.
Requirements of AD 96-23-02
Actions for Groups 1 Through 10, and 17 Through 36, as Specified in
Boeing Alert Service Bulletin 747-53A2409, Revision 5
(f) For airplanes identified as Groups 1 through 10 inclusive,
and 17 through 36 inclusive, in Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005: Do the inspections in
paragraph (f)(1) of this AD; and do the corrective action in
paragraph (f)(2) of this AD as applicable. Except as provided by
paragraph (i) of this AD, do all actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2409, dated September 26, 1996; or Revision 5, dated August 18,
2005. After the effective date of this AD, only Revision 5 of the
service bulletin may be used.
(1) At the applicable time in Figures 1, 2, 18, and 20 of
Revision 5 of the service bulletin, do initial and repetitive
inspections of Areas 1 and 4, as applicable, to detect disbonding,
corrosion, and cracking of the skin; except any inspection using
Method 1 or 2 must not be accomplished before the latest of the
following, as applicable: Before the accumulation of 2,000 total
flight cycles; 2,000 flight cycles since modification to the
stretched upper deck (SUD) configuration; or 2,000 flight cycles
since skin panel replacement in accordance with AD 90-26-10,
amendment 39-6836. If inspection Method 1 or 2 is used and no
disbonded doubler is found, no further action is required by this
AD.
(2) If any corrosion or cracking is found during any inspection
required by paragraph (f)(1) of this AD: Before further flight,
except as provided by paragraph (i) of this AD, repair and do any
applicable related investigative actions in accordance with the
Accomplishment Instructions of Revision 5 of the service bulletin.
New Requirements of This AD
Actions for Groups 11 Through 16 as Specified in Boeing Alert
Service Bulletin 747-53A2409, Revision 5 (Airplanes Added to the
Applicability of This AD)
(g) For airplanes identified as Groups 11 through 16 inclusive
in Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated
August 18, 2005: Do the inspections in paragraph (g)(1) of this AD;
and do the corrective action in paragraph (g)(2) of this AD as
applicable. Except as provided by paragraph (i) of this AD, do all
actions in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2409, Revision 5, dated August 18,
2005.
(1) At the applicable time in Figures 18 and 20 of the service
bulletin, do initial inspections of Area 4 and repetitive
inspections, as applicable, to detect disbonding, corrosion, and
cracking of the skin, as applicable; except any inspection using
Method 2 must not be accomplished before the latest of the
following, as applicable: Before the accumulation of 2,000 total
flight cycles; 2,000 flight cycles since modification to the SUD
configuration; or 2,000 flight cycles since skin panel replacement
in accordance with AD 90-26-10. If inspection Method 2 is used and
no disbonded doubler is found, no further action is required by this
AD.
(2) If any corrosion, disbonding, or cracking is found during
any inspection required by paragraph (g)(1) of this AD, before
further flight: Repair and do any applicable related investigative
actions in accordance with the Accomplishment Instructions of the
service bulletin.
Actions for Airplanes With Alodine-Coated Rivets for Groups 1
Through 10, and 17 Through 36 as Specified in Boeing Alert Service
Bulletin 747-53A2409, Revision 5
(h) For airplanes identified as Groups 1 through 10 inclusive,
and 17 through 36 inclusive, in Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005: Do the inspections in
paragraph (h)(1) of this AD; and do the corrective action in
paragraph (h)(2) of this AD if necessary. Except as provided by
paragraph (i) of this AD, do all actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005.
(1) At the applicable time in Figures 21 and 22 of the service
bulletin: Do initial and repetitive inspections of Areas 1 and 4, as
applicable, to detect cracking of the skin.
(2) If any cracking is found during any inspection required by
paragraph (h)(1) of this AD, before further flight: Repair in
accordance with the Accomplishment Instructions of the service
bulletin.
Exceptions
(i) Do all actions in accordance with the applicable service
bulletin except as provided by paragraphs (i)(1), (i)(2), (i)(3),
(i)(4), and (i)(5) of this AD.
(1) For the action in paragraph (f)(1) of this AD: Where Boeing
Alert Service Bulletin 747-53A2409, dated September 26, 1996; and
Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August
18, 2005; specify a compliance time after the issuance of any
revision of the service bulletin, this paragraph requires compliance
before the specified compliance time after November 27, 1996 (the
effective date of AD 96-23-02).
(2) For the actions in paragraphs (g)(1) and (h)(1) of this AD:
Where Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated
August 18, 2005, specifies a compliance time after the issuance or
receipt of any revision of the service bulletin, this paragraph
requires compliance before the specified compliance time after the
effective date of this AD.
(3) For any repair or any inspection where Boeing Alert Service
Bulletin 747-53A2409, Revision 5, dated August 18, 2005, specifies
to contact the manufacturer for further instructions: Before further
flight, repair or inspect using a method approved in accordance with
the procedures specified in paragraph (k) of this AD.
(4) If corrosion is found during any inspection required by this
AD, before further flight: Repair in accordance with an FAA-approved
method.
(5) Where Boeing Alert Service Bulletin 747-53A2409, Revision 5,
dated August 18, 2005, specifies that it is not necessary to count
flight cycles at 2.0 psi or less cabin differential pressure, this
AD does not allow for that adjustment factor.
Credit for Actions Accomplished Previously
(j) Actions done before the effective date of this AD in
accordance with the service bulletins specified in Table 1 of this
AD are acceptable for compliance with the corresponding requirements
of paragraphs (f) and (g) of this AD.
[[Page 56864]]
Table 1.--Credit Service Bulletins
------------------------------------------------------------------------
Revision
Service bulletin level Date
------------------------------------------------------------------------
Boeing Service Bulletin 747- 1 May 29, 1997.
53A2409.
Boeing Service Bulletin 747- 2 August 6, 1998.
53A2409.
Boeing Service Bulletin 747- 3 October 22, 1998.
53A2409.
Boeing Service Bulletin 747- 4 February 17, 2000.
53A2409.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(k)(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 Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 96-23-02,
are approved as AMOCs for the corresponding provisions of paragraph
(f) of this AD, except AMOCs for terminating action based upon
inspection results using a sliding probe low frequency eddy current
(LFEC), sliding probe high frequency eddy current (HFEC), or mid
frequency surface eddy current (MFEC) inspection methods; and
provided that any alternative method for future inspections did not
incorporate a sliding probe LFEC, sliding probe HFEC, or MFEC
inspection methods.
(4) 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
(l) You must use Boeing Alert Service Bulletin 747-53A2409,
dated September 26, 1996; or Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 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 Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On November 27, 1996 (61 FR 57994, November 12, 1996), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin 747-53A2409, dated
September 26, 1996.
(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 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 September 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-8227 Filed 9-27-06; 8:45 am]
BILLING CODE 4910-13-P
