Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400, 747SR, and 747SP Series Airplanes, 65403-65406 [E9-29222]
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Federal Register / Vol. 74, No. 236 / Thursday, December 10, 2009 / Rules and Regulations
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 this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
PART 39—AIRWORTHINESS
DIRECTIVES
FAA AD Differences
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2009–25–13 Bombardier, Inc. (Formerly
Avro International Aerospace Division;
British Aerospace, PLC; British
Aerospace Commercial Aircraft Limited;
British Aerospace (England)):
Amendment 39–16133. Docket No.
FAA–2009–1113; Directorate Identifier
2009–NM–238–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 28, 2009.
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Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier, Inc.
Model BD–100–1A10 (Challenger 300)
airplanes, certificated in any category;
equipped with sidewall heater having part
number (P/N) 3436–06–1/0.
Subject
(d) Air Transport Association (ATA) of
America Code 25: Equipment/Furnishings.
Reason
(e) The mandatory continued airworthiness
information (MCAI) states:
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16:49 Dec 09, 2009
Jkt 220001
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.
Actions
(g) Within 100 flight hours after the
effective date of this AD, deactivate the lefthand baggage bay sidewall heater having part
number (P/N) 3436–06–1/0, in accordance
with Bombardier Service Bulletin A100–25–
30, dated July 20, 2009.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
§ 39.13
There have been 3 reported occurrences of
uncontrolled excessive heat from the left
hand baggage bay sidewall heater, [part
number] P/N 3436–06–1/0, that resulted in
the affected sidewall heater panels sustaining
heat discoloration and/or scorching of the
liner material. The affected sidewall heater is
equipped with a thermostat to regulate
heating. These reported occurrences are the
subject of further investigation. As a
preventive measure, until such time as the
cause of the occurrences have been
determined, deactivation of the left hand
baggage bay heater is necessary to avoid the
potential for uncontrolled excessive heat by
the heater panel, and on the baggage bay
compartment, that could lead to flammability
issues.
The affected left hand baggage bay sidewall
heater, P/N 3436–06–1/0 is part of the Model
BD–100–1A10 aeroplane interior installation
approved under Transport Canada
Supplemental Type Certificate SA04–112.
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office, ANE–170, 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:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York,
11590; telephone 516–228–7300; fax 516–
794–5531. 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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
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65403
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(i) Refer to MCAI Canadian Airworthiness
Directive CF–2009–38, dated October 15,
2009; and Bombardier Service Bulletin
A100–25–30, dated July 20, 2009; for related
information.
Material Incorporated by Reference
(j) You must use Bombardier Service
Bulletin A100–25–30, dated July 20, 2009, 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
ˆ
this AD, contact Bombardier, Inc., 400 Cote
´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.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
December 1, 2009.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–29377 Filed 12–9–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0682; Directorate
Identifier 2008–NM–200–AD; Amendment
39–16131; AD 2009–25–11]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–300, 747–400,
747SR, and 747SP Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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Federal Register / Vol. 74, No. 236 / Thursday, December 10, 2009 / Rules and Regulations
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
747 airplanes. The existing AD currently
requires repetitive inspections for
cracking, and repair as necessary, of
lower lobe body frames (sections 42 and
46) of the fuselage. The existing AD also
provides for optional modification of
the frames, which terminates the
repetitive inspections. This new AD
requires additional repetitive
inspections for cracking of certain
fuselage frames, and corrective actions if
necessary. This AD results from a new
report of a crack found in a body frame
with a tapered side guide bracket at
fuselage station 1800, located on the left
side between stringers 39 and 40; the
frame was severed. We are issuing this
AD to detect and correct the loss of
structural integrity of the fuselage,
which could result in rapid
depressurization of the airplane.
DATES: This AD becomes effective
January 14, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of January 14, 2010.
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 86–18–01, amendment
39–5390 (51 FR 28691, August 11,
1986). The existing AD applies to
certain Boeing Model 747 airplanes.
That NPRM was published in the
Federal Register on August 5, 2009 (74
FR 38995). That NPRM proposed to
continue to require repetitive
inspections for cracking, and repair as
necessary, of lower lobe body frames
(sections 42 and 46) of the fuselage.
That NPRM also provides for optional
modification of the frames, which
terminates the repetitive inspections.
That NPRM also proposed to require
additional repetitive inspections for
cracking of certain fuselage frames, and
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 content of the NPRM.
Explanation of Change to Final Rule
AD 86–18–01 does not provide a
compliance time for doing the corrective
actions required by paragraphs (g) and
(h) of this AD. However, we have
determined that it is implicit in the
existing AD that the corrective actions
be done before further flight. Sections
91.7 and 121.153 of the Federal
Aviation Regulations (14 CFR 91.7 and
14 CFR 121.153) already require that
aircraft be in an airworthy condition
before they can be operated. We have
changed paragraphs (g) and (h) of this
AD to include those compliance times.
Conclusion
We reviewed the relevant data,
including the comment that has been
received, and determined that air safety
and the public interest require adopting
the AD with the change described
previously. We also determined that this
change will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
There are about 237 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
Work hours
Average
labor rate
per hour
Inspections (required by AD 86–18–01) .............
370
$80
Additional inspections (new action) .....................
6
80
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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,
VerDate Nov<24>2008
16:49 Dec 09, 2009
Jkt 220001
Cost per airplane
$29,600, per inspection
cycle.
$480, per inspection
cycle.
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
PO 00000
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Fmt 4700
Number of
U.S.registered
airplanes
Sfmt 4700
112
87
Fleet cost
$3,315,200, per inspection cycle.
$41,760, per inspection
cycle.
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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Federal Register / Vol. 74, No. 236 / Thursday, December 10, 2009 / Rules and Regulations
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
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 39–5390 (51
FR 28691, August 11, 1986) and by
adding the following new airworthiness
directive (AD):
■
2009–25–11 Boeing: Amendment 39–16131.
Docket No. FAA–2009–0682; Directorate
Identifier 2008–NM–200–AD.
Effective Date
(a) This AD becomes effective January 14,
2010.
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Affected ADs
(b) This AD supersedes AD 86–18–01,
Amendment 39–5390.
Applicability
(c) This AD applies to Boeing Model 747–
100, 747–100B, 747–100B SUD, 747–200B,
747–300, 747–400, 747SR, and 747SP series
airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin
747–53A2749, dated September 25, 2008.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from a report of a crack
found in a body frame with a tapered side
VerDate Nov<24>2008
16:49 Dec 09, 2009
Jkt 220001
guide bracket at fuselage station 1800,
located on the left side between stringers 39
and 40; the frame was severed. The Federal
Aviation Administration is issuing this AD to
detect and correct the loss of 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 86–18–
01, With Revised Service Information
Repetitive Inspections
(g) For airplanes listed in Boeing Alert
Service Bulletin 747–53A2237, Revision 1,
dated March 28, 1986: Perform a detailed
visual inspection for frame cracking from
fuselage section 540 to 760, and 1820 to
1900, stringers 35 left to 42 left, in
accordance with Section III of Boeing Alert
Service Bulletin 747–53A2237, Revision 1,
dated March 28, 1986. Do the inspection at
the time specified in paragraph (g)(1), (g)(2),
or (g)(3) of this AD, as applicable. If any crack
is found, before further flight, repair in
accordance with a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA, or using a method approved in
accordance with the procedures specified in
paragraph (p) of this AD. Repeat the
inspection at intervals not to exceed 3,000
landings until the terminating action
specified in paragraph (g)(4) or (k) of this AD
is performed.
(1) Within 300 landings for airplanes that
have accumulated more than 12,000 landings
on September 17, 1986 (the effective date of
AD 86–18–01, amendment 39–5390).
(2) Within 800 landings for airplanes that
have accumulated 10,000 to 12,000 landings
on September 17, 1986.
(3) Within 800 landings or prior to the
accumulation of 10,000 landings, whichever
occurs later, for airplanes that have
accumulated less than 10,000 landings on
September 17, 1986.
(4) Modification of the frames before the
effective date of this AD in accordance with
Boeing Alert Service Bulletin 747–53A2237,
Revision 1, dated March 28, 1986, constitutes
terminating action for the repetitive
inspections required by paragraph (g) of this
AD.
(h) For airplanes listed in Boeing Alert
Service Bulletin 747–53A2259, Revision 1,
dated April 18, 1986: Perform a visual
inspection of cargo side guide support
brackets from fuselage station 1500 to 1800,
right and left hand side, for a proper
machined taper in accordance with Section
III of Boeing Alert Service Bulletin 747–
53A2259, Revision 1, dated April 18, 1986.
Do the inspection at the time specified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD,
as applicable. If any cargo side guide support
bracket is improperly tapered, before further
flight, perform a detailed visual inspection of
the frame area adjacent to the untapered
bracket for cracking in accordance with
Boeing Alert Service Bulletin 747–53A2259,
Revision 1, dated April 18, 1986. If any crack
is found, before further flight, repair in
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Fmt 4700
Sfmt 4700
65405
accordance with a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA, or using a method approved in
accordance with the procedures specified in
paragraph (p) of this AD. Repeat the detailed
visual inspection at intervals not to exceed
3,000 landings until the terminating action
specified in paragraph (h)(4) of this AD is
performed. Accomplishment of the
inspections required by paragraph (k) of this
AD terminates the inspections required by
this paragraph.
(1) Within 300 landings for airplanes that
have accumulated more than 12,000 landings
on September 17, 1986 (the effective date of
AD 86–18–01, amendment 39–5390).
(2) Within 800 landings for airplanes that
have accumulated 10,000 to 12,000 landings
on September 17, 1986.
(3) Within 800 landings or prior to the
accumulation of 10,000 landings, whichever
occurs later, for airplanes that have
accumulated less than 10,000 landings on
September 17, 1986.
(4) Installation of a tapered strap adjacent
to the affected brackets before the effective
date of this AD in accordance with Boeing
Alert Service Bulletin 747–53A2259,
Revision 1, dated April 18, 1986, constitutes
terminating action for the repetitive
inspections required by paragraph (h) of this
AD.
(i) For Boeing Model 747SR airplanes only,
based on continued mixed operation of cabin
pressure differentials, the initial inspection
thresholds and reinspection intervals
specified in AD 86–18–01 may be multiplied
by a 1.2 adjustment factor. This provision is
not applicable to paragraphs (k), (m), and (n)
of this AD.
(j) For the purposes of complying with AD
86–18–01, the number of landings may be
determined to equal the number of
pressurization cycles where the cabin
pressure differential was greater than 2.0
pounds per square inch. This provision is not
applicable to paragraphs (k), (m), and (n) of
this AD.
New Requirements of This AD
Repetitive Inspections
(k) For airplanes identified in Boeing Alert
Service Bulletin 747–53A2749, dated
September 25, 2008, that have accumulated
22,000 or fewer total flight cycles as of the
effective date of this AD: Do initial and
repetitive detailed inspections for frame
cracking from fuselage body stations 1500 to
1800, stringers 39 to 40, by doing all the
actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2749, dated September 25, 2008,
except as required by paragraph (l) of this
AD. Do the inspections and corrective actions
at the times specified in paragraph 1.E. of
Boeing Alert Service Bulletin 747–53A2749,
dated September 25, 2008, except as required
by paragraphs (m) and (n) of this AD.
Accomplishment of the inspections required
by this paragraph terminates the inspections
required by paragraph (h) of this AD.
Exceptions to Service Bulletin Procedures
(l) If any crack is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin 747–53A2749, dated
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Federal Register / Vol. 74, No. 236 / Thursday, December 10, 2009 / Rules and Regulations
September 25, 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.
(m) Where Boeing Alert Service Bulletin
747–53A2749, dated September 25, 2008,
specifies a compliance time after the date of
the service bulletin, this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(n) Where Boeing Alert Service Bulletin
747–53A2749, dated September 25, 2008,
specifies a compliance time related to
accomplishing an action ‘‘as given in Boeing
Service Bulletin 747–53A2259,’’ this AD
requires compliance within the specified
compliance time after the applicable
compliance time required by paragraph (h) of
this AD.
Terminating Action
(o) Accomplishing the repetitive frame
inspections required by AD 2006–05–02,
amendment 39–14499; or AD 2005–20–30,
amendment 39–14327; terminates the
inspections required by paragraphs (g), (h),
and (k) of this AD.
Alternative Methods of Compliance
(AMOCs)
(p)(1) The Manager, Seattle Aircraft
Certification Office (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.
(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 paragraph (A) of AD 86–18–
01, are approved as alternative methods of
compliance with the corresponding
requirements of paragraph (g) of this AD.
(4) AMOCs approved previously in
accordance with paragraph (B) of AD 86–18–
01, are approved as alternative methods of
compliance with the corresponding
requirements of paragraph (h) of this AD.
(5) 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
(q) You must use the service information
contained in Table 1 of this AD, as
applicable, to do the actions required by this
AD, unless the AD specifies otherwise.
TABLE 1—MATERIAL INCORPORATED BY REFERENCE
Document
Revision
Date
Boeing Alert Service Bulletin 747–53A2237 ........................................................
Boeing Alert Service Bulletin 747–53A2259 ........................................................
Boeing Alert Service Bulletin 747–53A2749 ........................................................
1 ............................................................
1 ............................................................
Original ..................................................
March 28, 1986.
April 18, 1986.
September 25, 2008.
Page Nos.
Revision level shown on page
Date shown on page
2, 3, 5, 6, 9–11, 15, 16, 18–24 ............................................................................
1, 4, 7, 8, 12–14, 17, 25, 26 ................................................................................
Original ..................................................
Revision 1 .............................................
mstockstill on DSKH9S0YB1PROD with RULES
Boeing Alert Service Bulletin 747–53A2259,
Revision 1, dated April 18, 1986, contains the
following effective pages:
(1) The Director of the Federal Register
approved the incorporation by reference of
the 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.
VerDate Nov<24>2008
16:49 Dec 09, 2009
Jkt 220001
Issued in Renton, Washington, on
December 1, 2009.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–29222 Filed 12–9–09; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
March 28, 1986.
April 18, 1986.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1112; Directorate
Identifier 2009–NM–237–AD; Amendment
39–16132; AD 2009–25–12]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200 and –300 Series Airplanes;
Model A340–200 and –300 Series
Airplanes; and Model A340–500 and
–600 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
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Agencies
[Federal Register Volume 74, Number 236 (Thursday, December 10, 2009)]
[Rules and Regulations]
[Pages 65403-65406]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-29222]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0682; Directorate Identifier 2008-NM-200-AD;
Amendment 39-16131; AD 2009-25-11]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-300, 747-400, 747SR, and 747SP Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
[[Page 65404]]
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747 airplanes. The existing
AD currently requires repetitive inspections for cracking, and repair
as necessary, of lower lobe body frames (sections 42 and 46) of the
fuselage. The existing AD also provides for optional modification of
the frames, which terminates the repetitive inspections. This new AD
requires additional repetitive inspections for cracking of certain
fuselage frames, and corrective actions if necessary. This AD results
from a new report of a crack found in a body frame with a tapered side
guide bracket at fuselage station 1800, located on the left side
between stringers 39 and 40; the frame was severed. We are issuing this
AD to detect and correct the loss of structural integrity of the
fuselage, which could result in rapid depressurization of the airplane.
DATES: This AD becomes effective January 14, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of January 14,
2010.
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 86-18-01, amendment 39-
5390 (51 FR 28691, August 11, 1986). The existing AD applies to certain
Boeing Model 747 airplanes. That NPRM was published in the Federal
Register on August 5, 2009 (74 FR 38995). That NPRM proposed to
continue to require repetitive inspections for cracking, and repair as
necessary, of lower lobe body frames (sections 42 and 46) of the
fuselage. That NPRM also provides for optional modification of the
frames, which terminates the repetitive inspections. That NPRM also
proposed to require additional repetitive inspections for cracking of
certain fuselage frames, and 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 content of the NPRM.
Explanation of Change to Final Rule
AD 86-18-01 does not provide a compliance time for doing the
corrective actions required by paragraphs (g) and (h) of this AD.
However, we have determined that it is implicit in the existing AD that
the corrective actions be done before further flight. Sections 91.7 and
121.153 of the Federal Aviation Regulations (14 CFR 91.7 and 14 CFR
121.153) already require that aircraft be in an airworthy condition
before they can be operated. We have changed paragraphs (g) and (h) of
this AD to include those compliance times.
Conclusion
We reviewed the relevant data, including the comment that has been
received, and determined that air safety and the public interest
require adopting the AD with the change described previously. We also
determined that this change will not increase the economic burden on
any operator or increase the scope of the AD.
Costs of Compliance
There are about 237 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Cost per airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 86- 370 $80 $29,600, per 112 $3,315,200, per
18-01). inspection cycle. inspection cycle.
Additional inspections (new 6 80 $480, per 87 $41,760, per
action). inspection cycle. inspection cycle.
----------------------------------------------------------------------------------------------------------------
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
[[Page 65405]]
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 39-5390 (51 FR 28691, August 11, 1986) and by adding
the following new airworthiness directive (AD):
2009-25-11 Boeing: Amendment 39-16131. Docket No. FAA-2009-0682;
Directorate Identifier 2008-NM-200-AD.
Effective Date
(a) This AD becomes effective January 14, 2010.
Affected ADs
(b) This AD supersedes AD 86-18-01, Amendment 39-5390.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300, 747-400, 747SR, and 747SP series airplanes,
certificated in any category, as identified in Boeing Alert Service
Bulletin 747-53A2749, dated September 25, 2008.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from a report of a crack found in a body
frame with a tapered side guide bracket at fuselage station 1800,
located on the left side between stringers 39 and 40; the frame was
severed. The Federal Aviation Administration is issuing this AD to
detect and correct the loss of 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 86-18-01, With Revised Service
Information
Repetitive Inspections
(g) For airplanes listed in Boeing Alert Service Bulletin 747-
53A2237, Revision 1, dated March 28, 1986: Perform a detailed visual
inspection for frame cracking from fuselage section 540 to 760, and
1820 to 1900, stringers 35 left to 42 left, in accordance with
Section III of Boeing Alert Service Bulletin 747-53A2237, Revision
1, dated March 28, 1986. Do the inspection at the time specified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable. If
any crack is found, before further flight, repair in accordance with
a method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA, or using a method approved in accordance with the
procedures specified in paragraph (p) of this AD. Repeat the
inspection at intervals not to exceed 3,000 landings until the
terminating action specified in paragraph (g)(4) or (k) of this AD
is performed.
(1) Within 300 landings for airplanes that have accumulated more
than 12,000 landings on September 17, 1986 (the effective date of AD
86-18-01, amendment 39-5390).
(2) Within 800 landings for airplanes that have accumulated
10,000 to 12,000 landings on September 17, 1986.
(3) Within 800 landings or prior to the accumulation of 10,000
landings, whichever occurs later, for airplanes that have
accumulated less than 10,000 landings on September 17, 1986.
(4) Modification of the frames before the effective date of this
AD in accordance with Boeing Alert Service Bulletin 747-53A2237,
Revision 1, dated March 28, 1986, constitutes terminating action for
the repetitive inspections required by paragraph (g) of this AD.
(h) For airplanes listed in Boeing Alert Service Bulletin 747-
53A2259, Revision 1, dated April 18, 1986: Perform a visual
inspection of cargo side guide support brackets from fuselage
station 1500 to 1800, right and left hand side, for a proper
machined taper in accordance with Section III of Boeing Alert
Service Bulletin 747-53A2259, Revision 1, dated April 18, 1986. Do
the inspection at the time specified in paragraph (h)(1), (h)(2), or
(h)(3) of this AD, as applicable. If any cargo side guide support
bracket is improperly tapered, before further flight, perform a
detailed visual inspection of the frame area adjacent to the
untapered bracket for cracking in accordance with Boeing Alert
Service Bulletin 747-53A2259, Revision 1, dated April 18, 1986. If
any crack is found, before further flight, repair in accordance with
a method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA, or using a method approved in accordance with the
procedures specified in paragraph (p) of this AD. Repeat the
detailed visual inspection at intervals not to exceed 3,000 landings
until the terminating action specified in paragraph (h)(4) of this
AD is performed. Accomplishment of the inspections required by
paragraph (k) of this AD terminates the inspections required by this
paragraph.
(1) Within 300 landings for airplanes that have accumulated more
than 12,000 landings on September 17, 1986 (the effective date of AD
86-18-01, amendment 39-5390).
(2) Within 800 landings for airplanes that have accumulated
10,000 to 12,000 landings on September 17, 1986.
(3) Within 800 landings or prior to the accumulation of 10,000
landings, whichever occurs later, for airplanes that have
accumulated less than 10,000 landings on September 17, 1986.
(4) Installation of a tapered strap adjacent to the affected
brackets before the effective date of this AD in accordance with
Boeing Alert Service Bulletin 747-53A2259, Revision 1, dated April
18, 1986, constitutes terminating action for the repetitive
inspections required by paragraph (h) of this AD.
(i) For Boeing Model 747SR airplanes only, based on continued
mixed operation of cabin pressure differentials, the initial
inspection thresholds and reinspection intervals specified in AD 86-
18-01 may be multiplied by a 1.2 adjustment factor. This provision
is not applicable to paragraphs (k), (m), and (n) of this AD.
(j) For the purposes of complying with AD 86-18-01, the number
of landings may be determined to equal the number of pressurization
cycles where the cabin pressure differential was greater than 2.0
pounds per square inch. This provision is not applicable to
paragraphs (k), (m), and (n) of this AD.
New Requirements of This AD
Repetitive Inspections
(k) For airplanes identified in Boeing Alert Service Bulletin
747-53A2749, dated September 25, 2008, that have accumulated 22,000
or fewer total flight cycles as of the effective date of this AD: Do
initial and repetitive detailed inspections for frame cracking from
fuselage body stations 1500 to 1800, stringers 39 to 40, by doing
all the actions specified in the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2749, dated September 25, 2008,
except as required by paragraph (l) of this AD. Do the inspections
and corrective actions at the times specified in paragraph 1.E. of
Boeing Alert Service Bulletin 747-53A2749, dated September 25, 2008,
except as required by paragraphs (m) and (n) of this AD.
Accomplishment of the inspections required by this paragraph
terminates the inspections required by paragraph (h) of this AD.
Exceptions to Service Bulletin Procedures
(l) If any crack is found during any inspection required by this
AD, and Boeing Alert Service Bulletin 747-53A2749, dated
[[Page 65406]]
September 25, 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.
(m) Where Boeing Alert Service Bulletin 747-53A2749, dated
September 25, 2008, specifies a compliance time after the date of
the service bulletin, this AD requires compliance within the
specified compliance time after the effective date of this AD.
(n) Where Boeing Alert Service Bulletin 747-53A2749, dated
September 25, 2008, specifies a compliance time related to
accomplishing an action ``as given in Boeing Service Bulletin 747-
53A2259,'' this AD requires compliance within the specified
compliance time after the applicable compliance time required by
paragraph (h) of this AD.
Terminating Action
(o) Accomplishing the repetitive frame inspections required by
AD 2006-05-02, amendment 39-14499; or AD 2005-20-30, amendment 39-
14327; terminates the inspections required by paragraphs (g), (h),
and (k) of this AD.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, Seattle Aircraft Certification Office (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 paragraph (A)
of AD 86-18-01, are approved as alternative methods of compliance
with the corresponding requirements of paragraph (g) of this AD.
(4) AMOCs approved previously in accordance with paragraph (B)
of AD 86-18-01, are approved as alternative methods of compliance
with the corresponding requirements of paragraph (h) of this AD.
(5) 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
(q) You must use the service information contained in Table 1 of
this AD, as applicable, to do the actions required by this AD,
unless the AD specifies otherwise.
Table 1--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 747-53A2237 1........................... March 28, 1986.
Boeing Alert Service Bulletin 747-53A2259 1........................... April 18, 1986.
Boeing Alert Service Bulletin 747-53A2749 Original.................... September 25, 2008.
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 747-53A2259, Revision 1, dated April
18, 1986, contains the following effective pages:
----------------------------------------------------------------------------------------------------------------
Page Nos. Revision level shown on page Date shown on page
----------------------------------------------------------------------------------------------------------------
2, 3, 5, 6, 9-11, 15, 16, 18-24.......... Original.................... March 28, 1986.
1, 4, 7, 8, 12-14, 17, 25, 26............ Revision 1.................. April 18, 1986.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the 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 December 1, 2009.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-29222 Filed 12-9-09; 8:45 am]
BILLING CODE 4910-13-P