Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, -200B, and -300 Series Airplanes; and Model 747SP and 747SR Series Airplanes, 43629-43632 [E9-20579]
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Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations
TABLE 4—DOCUMENTS INCORPORATED BY REFERENCE FOR ACTIONS REQUIRED BY THIS AD
Service bulletin
Date
Fokker Service Bulletin SBF50–24–031 ..................................................................................................................................
Fokker Service Bulletin SBF100–24–041 ................................................................................................................................
Goodrich Power Systems Service Bulletin SG02206–24–01 .................................................................................................
January 29, 2008.
January 29, 2008.
March 4, 2008.
TABLE 5—DOCUMENTS INCORPORATED BY REFERENCE FOR OPTIONAL ACTIONS SPECIFIED IN THIS AD
Service bulletin
Date
Fokker Service Bulletin SBF50–24–030 including the drawings identified in Table 2 of this AD ..........................................
Fokker Service Bulletin SBF100–24–037, including Manual Change Notification—Maintenance Documentation MCNM
F100–076, dated October 2, 2003, and including the drawings identified in Table 3 of this AD.
Issued in Renton, Washington, on August
17, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–20576 Filed 8–26–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0477; Directorate
Identifier 2008–NM–191–AD; Amendment
39–16003; AD 2009–18–07]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, –100B, –100B SUD,
–200B, and –300 Series Airplanes; and
Model 747SP and 747SR Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747 series airplanes. That AD currently
requires repetitive inspections to detect
cracks in various areas of the fuselage
internal structure, and related
investigative/corrective actions if
necessary. This new AD requires
additional repetitive inspections for
cracking of certain fuselage structure,
and related investigative/corrective
actions if necessary. This AD results
from fatigue tests and analysis by
Boeing that identified areas of the
fuselage where fatigue cracks can occur.
VerDate Nov<24>2008
16:19 Aug 26, 2009
Jkt 217001
We are issuing this AD to prevent the
loss of the structural integrity of the
fuselage, which could result in rapid
depressurization of the airplane.
DATES: This AD becomes effective
October 1, 2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 1, 2009.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1, fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
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:
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November 6, 2003.
October 2, 2003.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2005–20–30, amendment
39–14327 (70 FR 59252, October 12,
2005). The existing AD applies to
certain Boeing Model 747 series
airplanes. That NPRM was published in
the Federal Register on May 26, 2009
(74 FR 24712). That NPRM proposed to
continue to require repetitive
inspections to detect cracks in various
areas of the fuselage internal structure,
and related investigative/corrective
actions if necessary. That NPRM also
proposed to require additional repetitive
inspections for cracking of certain
fuselage structure, and related
investigative/corrective actions if
necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that has been
received on the NPRM. Boeing concurs
with the NPRM.
Conclusion
We have carefully reviewed the
available data, including the comment
that has been received, and determined
that air safety and the public interest
require adopting the AD as proposed.
Costs of Compliance
There are about 209 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.
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Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations
TABLE—ESTIMATED COSTS
Work
hours
Action
Inspections (required by AD 2005–20–30) ..........................................................................
Additional inspections in Area 1 (new action) .....................................................................
Additional inspections in Area 6 (new action) .....................................................................
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.
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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.
VerDate Nov<24>2008
16:19 Aug 26, 2009
Jkt 217001
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14327 (70
FR 59252, October 12, 2005) and by
adding the following new airworthiness
directive (AD):
■
2009–18–07 Boeing: Amendment 39–16003.
Docket No. FAA–2009–0477; Directorate
Identifier 2008–NM–191–AD.
Effective Date
(a) This AD becomes effective October 1,
2009.
Affected ADs
(b) This AD supersedes AD 2005–20–30.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–300, 747SP, and 747SR series airplanes;
certificated in any category; identified in
Boeing Service Bulletin 747–53A2349,
Revision 3, dated October 2, 2008.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from fatigue tests and
analysis by Boeing that identified areas of the
fuselage where fatigue cracks can occur. We
are issuing this AD to prevent the loss of the
structural integrity of the fuselage, which
could result in rapid depressurization of the
airplane.
Compliance
(f) 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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Number of
U.S.-registered
airplanes
Fleet cost
$10,400
480
80
69
69
69
$717,600
33,120
5,520
130
6
1
Adoption of the Amendment
Authority for This Rulemaking
Cost per airplane, per inspection cycle
Restatement of Requirements of AD 2002–
10–10 With Revised Service Information
(Excluding Upper Deck Floor Beams)
Repetitive Inspections
(g) Prior to the accumulation of 22,000 total
flight cycles, or within 1,000 flight cycles
after June 11, 1993 (the effective date of AD
93–08–12, amendment 39–8559, which was
superseded by AD 2002–10–10), whichever
occurs later, unless accomplished previously
within the last 2,000 flight cycles; and
thereafter at intervals not to exceed 3,000
flight cycles: Perform an internal detailed
inspection to detect cracks in the areas of the
fuselage internal structure specified in
paragraphs (g)(1) through (g)(6) of this AD; in
accordance with Boeing Service Bulletin
747–53–2349, dated June 27, 1991; Boeing
Alert Service Bulletin 747–53A2349,
Revision 1, dated October 12, 2000; Boeing
Service Bulletin 747–53A2349, Revision 2,
dated April 3, 2003; or Boeing Alert Service
Bulletin 747–53A2349, Revision 3, dated
October 2, 2008. After the effective date of
this AD, only Revision 3 of Boeing Alert
Service Bulletin 747–53A2349 may be used.
Continue doing the inspections until the
inspections required by paragraph (j) of this
AD are done.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Section 41 body station 260, 340, and
400 bulkheads.
(6) Main entry doors.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(h) Prior to the accumulation of 25,000
total flight cycles, or within 1,000 flight
cycles after June 11, 1993, whichever is later,
unless already done within the last 2,000
flight cycles; and thereafter at intervals not to
exceed 3,000 flight cycles: Do an internal
detailed inspection to detect cracks in the
Section 46 upper lobe frames, in accordance
with Boeing Service Bulletin 747–53–2349,
dated June 27, 1991; Boeing Alert Service
Bulletin 747–53A2349, Revision 1, dated
October 12, 2000; Boeing Service Bulletin
747–53A2349, Revision 2, dated April 3,
2003; or Boeing Alert Service Bulletin 747–
53A2349, Revision 3, dated October 2, 2008.
After the effective date of this AD, only
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Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations
Revision 3 of Boeing Alert Service Bulletin
747–53A2349 may be used.
Repair of Cracks Detected During Paragraph
(g) or (h) Inspections
(i) Before further flight, repair any cracks
detected during the inspections done per
paragraph (g) or (h) of this AD by doing the
actions specified in paragraph (i)(1) or (i)(2)
of this AD, as applicable.
(1) Repair in accordance with a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or using a
method approved in accordance with
paragraph (p) of this AD.
(2) Repair in accordance with Boeing
Service Bulletin 747–53A2349, Revision 2,
dated April 3, 2003; or Boeing Alert Service
Bulletin 747–53A2349, Revision 3, dated
October 2, 2008. After the effective date of
this AD, only Revision 3 of Boeing Alert
Service Bulletin 747–53A2349 may be used.
Where either revision of the service bulletin
specifies to contact Boeing for repair
instructions, repair in accordance with a
method approved by the Manager, Seattle
ACO; or use a method approved in
accordance with paragraph (p) of this AD.
Restatement of Requirements of AD 2005–
20–30 With Revised Service Information
Repetitive Inspections
(j) Do an internal detailed inspection to
detect cracking in the areas of the fuselage
internal structure specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD, and internal
and external detailed inspections of the areas
specified in paragraphs (j)(4), (j)(5), (j)(6), and
(j)(7) of this AD. Do the inspections in
accordance with Boeing Service Bulletin
747–53A2349, Revision 2, dated April 3,
2003; or Boeing Alert Service Bulletin 747–
53A2349, Revision 3, dated October 2, 2008.
After the effective date of this AD, only
Revision 3 of Boeing Alert Service Bulletin
747–53A2349 may be used. Do the
inspections at the applicable time specified
in paragraph (k) of this AD. Accomplishment
of these inspections terminates the
requirements of paragraph (g) of this AD.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Nose wheel well bulkheads, sidewall
panels, and station (STA) 360 and 380 floor
beams. These areas include Section 41 body
station 260, 340, and 400 bulkheads.
(6) Main entry doors.
(7) Main electronics bay access door
cutout.
(k) Do the inspections required by
paragraph (j) of this AD at the applicable time
specified in paragraph (k)(1), (k)(2), or (k)(3)
of this AD. Repeat the inspections thereafter
at intervals not to exceed 3,000 flight cycles.
(1) For airplanes on which the inspections
required by paragraphs (g)(1), (g)(2), (g)(3),
(g)(4), and (g)(6) of this AD have been done
before November 16, 2005 (the effective date
of AD 2005–20–30), but the inspections
required by paragraphs (j)(5) and (j)(7) of this
AD have not been done: Within 3,000 flight
cycles since accomplishment of the most
recent inspection required by paragraphs
(g)(1), (g)(2), (g)(3), (g)(4), and (g)(6) of this
AD, except that the inspections specified in
paragraphs (j)(5) and (j)(7) of this AD may be
done within 3,000 flight cycles since
accomplishment of the most recent
inspection required by paragraphs (g)(1),
(g)(2), (g)(3), (g)(4), and (g)(6) of this AD, or
within 1,000 flight cycles after November 16,
2005, whichever is later.
(2) For airplanes on which the inspections
required by paragraphs (j)(5) and (j)(7) have
been done before November 16, 2005: Within
3,000 flight cycles since accomplishment of
the most recent inspection required by
paragraphs (j)(5) and (j)(7) of this AD, or
43631
within 1,000 flight cycles after November 16,
2005, whichever is later.
(3) For airplanes on which the inspections
required by paragraph (g) of this AD have not
been done before November 16, 2005: Prior
to the accumulation of 22,000 total flight
cycles, or within 1,000 flight cycles after
November 16, 2005, whichever is later.
Repair of Cracks Detected During Paragraph
(j) Inspection
(l) Before further flight, repair any cracking
found during any inspection required by
paragraph (j) of this AD in accordance with
Boeing Service Bulletin 747–53A2349,
Revision 2, dated April 3, 2003; or Boeing
Alert Service Bulletin 747–53A2349,
Revision 3, dated October 2, 2008. After the
effective date of this AD, only Revision 3 of
Boeing Alert Service Bulletin 747–53A2349
may be used. Where any revision of the
service bulletin specifies to contact Boeing
for repair instructions, repair in accordance
with a method approved by the Manager,
Seattle ACO; or use a method approved in
accordance with paragraph (p) of this AD.
New Requirements of This AD
Inspections and Repair
(m) Do initial and repetitive detailed
inspections for cracking in the areas specified
in Table 1 of this AD using applicable
internal and external detailed inspection
methods; and repair all cracks, by doing all
the applicable actions in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2349, Revision 3,
dated October 2, 2008, except as required by
paragraph (n) of this AD. Do the initial and
repetitive inspections at the times specified
in paragraph 1.E., ‘‘Compliance,’’ of the
service bulletin, except as required by
paragraph (o) of this AD. Repair all cracks
before further flight after detection.
TABLE 1—ADDITIONAL INSPECTIONS
Inspect the addition portion of area 1 and area 6 as specified in Boeing Alert Service Bulletin 747–
53A2349, Revision 3, dated October 2, 2008 (‘‘the service bulletin’’)—
For airplanes identified as these groups
in the service bulletin—
In Area 1: Fuselage frames at body stations 260–520 in areas where the upper deck floor beams are
attached (Figure 11 of the Accomplishments Instructions of the service bulletin).
In Area 6: Fuselage frames at body stations 400–500 in areas above the Main Entry Door 1 cutouts,
from the upper chord of the upper deck floor beams to Stringer 8 (Figure 12 of the Accomplishment
Instructions of the service bulletin).
1 through 7 inclusive.
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Exceptions to Certain Procedures
(n) If any crack is found during any
inspection required by paragraph (m) of this
AD, and Boeing Alert Service Bulletin 747–
53A2349, Revision 3, dated October 2, 2008,
specifies to contact Boeing for appropriate
action: Before further flight, repair the crack
using a method approved in accordance with
the procedures specified in paragraph (p) of
this AD.
(o) Where Boeing Alert Service Bulletin
747–53A2349, Revision 3, dated October 2,
2008, specifies a compliance time after the
date on Boeing Alert Service Bulletin 747–
53A2349, Revision 3, dated October 2, 2008,
this AD requires compliance within the
VerDate Nov<24>2008
16:19 Aug 26, 2009
Jkt 217001
specified compliance time after the effective
date of this AD.
Alternative Methods of Compliance
(AMOCs)
(p)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. Send information to ATTN: 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. Or, email information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov.
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6 and 7.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(3) AMOCs approved previously in
accordance with AD 2005–20–30 are
approved as AMOCs with the corresponding
provisions of this AD.
(4) An AMOC that provides an acceptable
level of safety may be used for any repair
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Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations
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
(q) You must use Boeing Alert Service
Bulletin 747–53A2349, Revision 3, dated
October 2, 2008, as applicable, to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1, fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
17, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–20579 Filed 8–26–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0386; Directorate
Identifier 2008–NM–184–AD; Amendment
39–16002; AD 2009–18–06]
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RIN 2120–AA64
Airworthiness Directives;
Construcciones Aeronauticas, S.A.
(CASA), Model CN–235, CN–235–100,
CN–235–200, and CN–235–300
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
VerDate Nov<24>2008
16:19 Aug 26, 2009
Jkt 217001
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
During operation in icing conditions, an
asymmetric configuration of the de-icing
boots was detected, occurring during the
inflation and deflation check of the de-icing
system. This was found to be due to an
unexpected failure mode in the pneumatic
and de-icing system’s control electronic
logic. This condition, if not corrected, could
affect the de-icing capabilities of the boots
installed on the wing and horizontal
stabilizers, potentially leading to loss of
control of the aircraft.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 1, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 1, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM–
116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1112; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on April 29, 2009 (74 FR
19460). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
During operation in icing conditions, an
asymmetric configuration of the de-icing
boots was detected, occurring during the
inflation and deflation check of the de-icing
system. This was found to be due to an
unexpected failure mode in the pneumatic
and de-icing system’s control electronic
logic. This condition, if not corrected, could
affect the de-icing capabilities of the boots
installed on the wing and horizontal
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Sfmt 4700
stabilizers, potentially leading to loss of
control of the aircraft.
To address and correct this unsafe
condition, EADS–CASA developed
modification 31558, approved by DGAC–
Spain and incorporated into the Type Design
Definition through the approval of CN–235–
300 version AE02, revision 14 of Spanish
Type Certificate DGAC 01/86, dated 22
March 2002, and modification 31607, Minor
Change approved by EADS–CASA under
their DOA 21J.032 privileges, complementary
to modification 31558. The entire
modification package consists of an
improvement of the de-icing boots electronic
control system, making it capable of
detecting all possible boot configurations on
wings and horizontal stabilizers without
affecting pneumatic system functions. The
instructions for the in-service
accomplishment of this modification have
been published as CN–235 Service Bulletin
(SB) 235–30–16 dated 21 January 2005.
For the reasons described above, this EASA
AD requires the modification of the De-Icing
Boots control system in all aircraft that have
not yet implemented the modification.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Change to Parts Cost
We have revised the parts cost to
reflect the price of two kits from the
manufacturer. The revised cost is less
than the original cost presented in the
NPRM.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 8
products of U.S. registry. We also
E:\FR\FM\27AUR1.SGM
27AUR1
]]>Agencies
[Federal Register Volume 74, Number 165 (Thursday, August 27, 2009)]
[Rules and Regulations]
[Pages 43629-43632]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20579]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0477; Directorate Identifier 2008-NM-191-AD;
Amendment 39-16003; AD 2009-18-07]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD,
-200B, and -300 Series Airplanes; and Model 747SP and 747SR Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747 series airplanes. That
AD currently requires repetitive inspections to detect cracks in
various areas of the fuselage internal structure, and related
investigative/corrective actions if necessary. This new AD requires
additional repetitive inspections for cracking of certain fuselage
structure, and related investigative/corrective actions if necessary.
This AD results from fatigue tests and analysis by Boeing that
identified areas of the fuselage where fatigue cracks can occur. We are
issuing this AD to prevent the loss of the structural integrity of the
fuselage, which could result in rapid depressurization of the airplane.
DATES: This AD becomes effective October 1, 2009.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 1,
2009.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
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:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2005-20-30, amendment
39-14327 (70 FR 59252, October 12, 2005). The existing AD applies to
certain Boeing Model 747 series airplanes. That NPRM was published in
the Federal Register on May 26, 2009 (74 FR 24712). That NPRM proposed
to continue to require repetitive inspections to detect cracks in
various areas of the fuselage internal structure, and related
investigative/corrective actions if necessary. That NPRM also proposed
to require additional repetitive inspections for cracking of certain
fuselage structure, and related investigative/corrective actions if
necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
received on the NPRM. Boeing concurs with the NPRM.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD as proposed.
Costs of Compliance
There are about 209 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.
[[Page 43630]]
Table--Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Work airplane, per Number of U.S.- Fleet
Action hours inspection registered cost
cycle airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2005-20-30)..................... 130 $10,400 69 $717,600
Additional inspections in Area 1 (new action)............... 6 480 69 33,120
Additional inspections in Area 6 (new action)............... 1 80 69 5,520
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14327 (70 FR 59252, October 12, 2005) and by
adding the following new airworthiness directive (AD):
2009-18-07 Boeing: Amendment 39-16003. Docket No. FAA-2009-0477;
Directorate Identifier 2008-NM-191-AD.
Effective Date
(a) This AD becomes effective October 1, 2009.
Affected ADs
(b) This AD supersedes AD 2005-20-30.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes;
certificated in any category; identified in Boeing Service Bulletin
747-53A2349, Revision 3, dated October 2, 2008.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from fatigue tests and analysis by Boeing
that identified areas of the fuselage where fatigue cracks can
occur. We are issuing this AD to prevent the loss of the structural
integrity of the fuselage, which could result in rapid
depressurization of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2002-10-10 With Revised Service
Information (Excluding Upper Deck Floor Beams)
Repetitive Inspections
(g) Prior to the accumulation of 22,000 total flight cycles, or
within 1,000 flight cycles after June 11, 1993 (the effective date
of AD 93-08-12, amendment 39-8559, which was superseded by AD 2002-
10-10), whichever occurs later, unless accomplished previously
within the last 2,000 flight cycles; and thereafter at intervals not
to exceed 3,000 flight cycles: Perform an internal detailed
inspection to detect cracks in the areas of the fuselage internal
structure specified in paragraphs (g)(1) through (g)(6) of this AD;
in accordance with Boeing Service Bulletin 747-53-2349, dated June
27, 1991; Boeing Alert Service Bulletin 747-53A2349, Revision 1,
dated October 12, 2000; Boeing Service Bulletin 747-53A2349,
Revision 2, dated April 3, 2003; or Boeing Alert Service Bulletin
747-53A2349, Revision 3, dated October 2, 2008. After the effective
date of this AD, only Revision 3 of Boeing Alert Service Bulletin
747-53A2349 may be used. Continue doing the inspections until the
inspections required by paragraph (j) of this AD are done.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Section 41 body station 260, 340, and 400 bulkheads.
(6) Main entry doors.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(h) Prior to the accumulation of 25,000 total flight cycles, or
within 1,000 flight cycles after June 11, 1993, whichever is later,
unless already done within the last 2,000 flight cycles; and
thereafter at intervals not to exceed 3,000 flight cycles: Do an
internal detailed inspection to detect cracks in the Section 46
upper lobe frames, in accordance with Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; Boeing Service Bulletin
747-53A2349, Revision 2, dated April 3, 2003; or Boeing Alert
Service Bulletin 747-53A2349, Revision 3, dated October 2, 2008.
After the effective date of this AD, only
[[Page 43631]]
Revision 3 of Boeing Alert Service Bulletin 747-53A2349 may be used.
Repair of Cracks Detected During Paragraph (g) or (h) Inspections
(i) Before further flight, repair any cracks detected during the
inspections done per paragraph (g) or (h) of this AD by doing the
actions specified in paragraph (i)(1) or (i)(2) of this AD, as
applicable.
(1) Repair in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or using a method
approved in accordance with paragraph (p) of this AD.
(2) Repair in accordance with Boeing Service Bulletin 747-
53A2349, Revision 2, dated April 3, 2003; or Boeing Alert Service
Bulletin 747-53A2349, Revision 3, dated October 2, 2008. After the
effective date of this AD, only Revision 3 of Boeing Alert Service
Bulletin 747-53A2349 may be used. Where either revision of the
service bulletin specifies to contact Boeing for repair
instructions, repair in accordance with a method approved by the
Manager, Seattle ACO; or use a method approved in accordance with
paragraph (p) of this AD.
Restatement of Requirements of AD 2005-20-30 With Revised Service
Information
Repetitive Inspections
(j) Do an internal detailed inspection to detect cracking in the
areas of the fuselage internal structure specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD, and internal and external
detailed inspections of the areas specified in paragraphs (j)(4),
(j)(5), (j)(6), and (j)(7) of this AD. Do the inspections in
accordance with Boeing Service Bulletin 747-53A2349, Revision 2,
dated April 3, 2003; or Boeing Alert Service Bulletin 747-53A2349,
Revision 3, dated October 2, 2008. After the effective date of this
AD, only Revision 3 of Boeing Alert Service Bulletin 747-53A2349 may
be used. Do the inspections at the applicable time specified in
paragraph (k) of this AD. Accomplishment of these inspections
terminates the requirements of paragraph (g) of this AD.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Nose wheel well bulkheads, sidewall panels, and station
(STA) 360 and 380 floor beams. These areas include Section 41 body
station 260, 340, and 400 bulkheads.
(6) Main entry doors.
(7) Main electronics bay access door cutout.
(k) Do the inspections required by paragraph (j) of this AD at
the applicable time specified in paragraph (k)(1), (k)(2), or (k)(3)
of this AD. Repeat the inspections thereafter at intervals not to
exceed 3,000 flight cycles.
(1) For airplanes on which the inspections required by
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), and (g)(6) of this AD
have been done before November 16, 2005 (the effective date of AD
2005-20-30), but the inspections required by paragraphs (j)(5) and
(j)(7) of this AD have not been done: Within 3,000 flight cycles
since accomplishment of the most recent inspection required by
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), and (g)(6) of this AD,
except that the inspections specified in paragraphs (j)(5) and
(j)(7) of this AD may be done within 3,000 flight cycles since
accomplishment of the most recent inspection required by paragraphs
(g)(1), (g)(2), (g)(3), (g)(4), and (g)(6) of this AD, or within
1,000 flight cycles after November 16, 2005, whichever is later.
(2) For airplanes on which the inspections required by
paragraphs (j)(5) and (j)(7) have been done before November 16,
2005: Within 3,000 flight cycles since accomplishment of the most
recent inspection required by paragraphs (j)(5) and (j)(7) of this
AD, or within 1,000 flight cycles after November 16, 2005, whichever
is later.
(3) For airplanes on which the inspections required by paragraph
(g) of this AD have not been done before November 16, 2005: Prior to
the accumulation of 22,000 total flight cycles, or within 1,000
flight cycles after November 16, 2005, whichever is later.
Repair of Cracks Detected During Paragraph (j) Inspection
(l) Before further flight, repair any cracking found during any
inspection required by paragraph (j) of this AD in accordance with
Boeing Service Bulletin 747-53A2349, Revision 2, dated April 3,
2003; or Boeing Alert Service Bulletin 747-53A2349, Revision 3,
dated October 2, 2008. After the effective date of this AD, only
Revision 3 of Boeing Alert Service Bulletin 747-53A2349 may be used.
Where any revision of the service bulletin specifies to contact
Boeing for repair instructions, repair in accordance with a method
approved by the Manager, Seattle ACO; or use a method approved in
accordance with paragraph (p) of this AD.
New Requirements of This AD
Inspections and Repair
(m) Do initial and repetitive detailed inspections for cracking
in the areas specified in Table 1 of this AD using applicable
internal and external detailed inspection methods; and repair all
cracks, by doing all the applicable actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2349, Revision 3, dated October 2, 2008, except as required by
paragraph (n) of this AD. Do the initial and repetitive inspections
at the times specified in paragraph 1.E., ``Compliance,'' of the
service bulletin, except as required by paragraph (o) of this AD.
Repair all cracks before further flight after detection.
Table 1--Additional Inspections
------------------------------------------------------------------------
Inspect the addition portion of area 1 and
area 6 as specified in Boeing Alert For airplanes identified as
Service Bulletin 747-53A2349, Revision 3, these groups in the service
dated October 2, 2008 (``the service bulletin--
bulletin'')--
------------------------------------------------------------------------
In Area 1: Fuselage frames at body 1 through 7 inclusive.
stations 260-520 in areas where the upper
deck floor beams are attached (Figure 11
of the Accomplishments Instructions of
the service bulletin).
In Area 6: Fuselage frames at body 6 and 7.
stations 400-500 in areas above the Main
Entry Door 1 cutouts, from the upper
chord of the upper deck floor beams to
Stringer 8 (Figure 12 of the
Accomplishment Instructions of the
service bulletin).
------------------------------------------------------------------------
Exceptions to Certain Procedures
(n) If any crack is found during any inspection required by
paragraph (m) of this AD, and Boeing Alert Service Bulletin 747-
53A2349, Revision 3, dated October 2, 2008, specifies to contact
Boeing for appropriate action: Before further flight, repair the
crack using a method approved in accordance with the procedures
specified in paragraph (p) of this AD.
(o) Where Boeing Alert Service Bulletin 747-53A2349, Revision 3,
dated October 2, 2008, specifies a compliance time after the date on
Boeing Alert Service Bulletin 747-53A2349, Revision 3, dated October
2, 2008, this AD requires compliance within the specified compliance
time after the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. Send information to ATTN: 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. Or, e-mail
information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(3) AMOCs approved previously in accordance with AD 2005-20-30
are approved as AMOCs with the corresponding provisions of this AD.
(4) An AMOC that provides an acceptable level of safety may be
used for any repair
[[Page 43632]]
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
(q) You must use Boeing Alert Service Bulletin 747-53A2349,
Revision 3, dated October 2, 2008, as applicable, to do the actions
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1, fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on August 17, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-20579 Filed 8-26-09; 8:45 am]
BILLING CODE 4910-13-P
