Airworthiness Directives; The Boeing Company Model 737-300, -400, and -500 Series Airplanes, 426-428 [2010-33003]
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426
Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations
TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE
Document
Date
Fokker Service Bulletin SBF100–27–091 ................................................................................................................................
Fokker Service Bulletin SBF100–27–092 ................................................................................................................................
Goodrich Service Bulletin 23100–27–29 .................................................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
Fokker Service Bulletin SBF100–27–092,
dated April 27, 2009; and Goodrich Service
Bulletin 23100–27–29, dated November 14,
2008; under 5 U.S.C. 552(a) and 1 CFR part
51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Fokker Service Bulletin SBF100–
27–091, dated August 31, 2007, on December
26, 2008 (73 FR 70261, November 20, 2008).
(3) For Fokker service information
identified in this AD, contact Fokker Services
B.V., Technical Services Dept., P.O. Box 231,
2150 AE Nieuw-Vennep, the Netherlands;
telephone +31 (0)252–627–350; fax +31
(0)252–627–211; e-mail
technicalservices.fokkerservices@stork.com;
Internet https://www.myfokkerfleet.com. For
Goodrich service information identified in
this AD, contact Goodrich Corporation,
Landing Gear, 1400 South Service Road,
West Oakville L6L 5Y7, Ontario, Canada;
telephone 905–825–1568; e-mail
jean.breed@goodrich.com; Internet https://
www.goodrich.com/TechPubs.
(4) 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.
(5) 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 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–32990 Filed 1–4–11; 8:45 am]
WReier-Aviles on DSKGBLS3C1PROD with RULES
BILLING CODE 4910–13–P
VerDate Mar<15>2010
15:20 Jan 04, 2011
Jkt 223001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0855; Directorate
Identifier 2010–NM–066–AD; Amendment
39–16566; AD 2011–01–12]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–300, –400, and
–500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
the products listed above. That AD
currently requires repetitive inspections
for discrepancies of the fuse pins of the
inboard and outboard midspar fittings of
the nacelle strut, and corrective actions
if necessary. This new AD requires
replacing the midspar fuse pins with
new, improved fuse pins, which would
terminate the repetitive inspections.
This AD was prompted by a report of
corrosion damage of the chrome runout
on the head side found on all four
midspar fuse pins of the nacelle strut.
Additionally, a large portion of the
chrome plate was missing from the
corroded area of the shank. We are
issuing this AD to prevent damage of the
fuse pins of the inboard and outboard
midspar fittings of the nacelle strut,
which could result in reduced structural
integrity of the fuse pins, and
consequent loss of the strut and
separation of the engine from the
airplane.
SUMMARY:
This AD is effective February 9,
2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of February 9, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 13, 2008 (73 FR
59493, October 9, 2008).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
DATES:
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
August 31, 2007.
April 27, 2009.
November 14, 2008.
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. You
may review copies of the referenced
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.
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 (phone: 800–647–5527) is
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:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6450; fax (425) 917–6590;
e-mail: alan.pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness
directive (AD) 2008–21–03, Amendment
39–15687 (73 FR 59493, October 9,
2008). That AD applies to the specified
products. The NPRM published in the
Federal Register on September 23, 2010
(75 FR 57882). That NPRM proposed to
continue to require repetitive
inspections for discrepancies of the fuse
pins of the inboard and outboard
midspar fittings of the nacelle strut, and
corrective actions if necessary. That
NPRM also proposed to require
replacing the midspar fuse pins with
new, improved fuse pins, which would
terminate the requirement for repetitive
detailed inspections.
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Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations
Comments
Conclusion
Costs of Compliance
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
Boeing supports the NPRM.
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
There are about 1,961 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
Repetitive detailed inspections
(required by AD 2008–21–
03).
Midspar fuse pin replacement
(new action).
Parts
Cost per
airplane
$85
None .................
85
4 .....................
$843 per pin .....
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),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
VerDate Mar<15>2010
15:20 Jan 04, 2011
Jkt 223001
Number
of U.S.registered
airplanes
$340, per inspection
cycle.
Up to $3,712 ..
1 per pin (up
to 4 pins per
airplane).
Authority for This Rulemaking
WReier-Aviles on DSKGBLS3C1PROD with RULES
Average
labor rate
per hour
Work hours
under the criteria of the Regulatory
Flexibility Act.
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:
■
Fleet cost
616
$209,440, per inspection cycle.
616
Up to $2,286,592.
Unsafe Condition
(e) This AD results from a report of
corrosion damage of the chrome runout on
the head side found on all four midspar fuse
pins of the nacelle strut. Additionally, a large
portion of the chrome plate was missing from
the corroded area of the shank. The Federal
Aviation Administration is issuing this AD to
prevent damage of the fuse pins of the
inboard and outboard midspar fittings of the
nacelle strut, which could result in reduced
structural integrity of the fuse pins, and
consequent loss of the strut and separation of
the engine from the airplane.
Compliance
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 FAA amends § 39.13 by
removing airworthiness directive (AD)
2008–21–03, Amendment 39–15687
(73 FR 59493, October 9, 2008), and
adding the following new AD:
■
2011–01–12 The Boeing Company:
Amendment 39–16566; Docket No.
FAA–2010–0855; Directorate Identifier
2010–NM–066–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective February 9, 2011.
Affected ADs
(b) This AD supersedes AD 2008–21–03,
Amendment 39–15687.
Applicability
(c) This AD applies to all The Boeing
Company Model 737–300, –400, and –500
series airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 54: Nacelles/Pylons.
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
(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 2008–
21–03
Repetitive Inspections/Corrective Actions,
With Revised Service Information
(g) At the applicable time specified in
paragraph 1.E., ‘‘Compliance’’ of Boeing
Special Attention Service Bulletin 737–54–
1044, dated December 10, 2007; except,
where that service bulletin specifies a
compliance time after the date on that service
bulletin, this AD requires compliance within
the specified compliance time after
November 13, 2008 (the effective date of AD
2008–21–03): Do a detailed inspection for
discrepancies of the fuse pins of the inboard
and outboard midspar fittings of the nacelle
strut by doing all the actions, including all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
737–54–1044, dated December 10, 2007; or
Boeing Alert Service Bulletin 737–54A1044,
Revision 2, dated January 20, 2010. Do all
applicable corrective actions before further
flight. Repeat the inspection at the time
specified in paragraph 1.E. of Boeing Special
Attention Service Bulletin 737–54–1044,
dated December 10, 2007. Accomplishing the
actions of paragraph (h) of this AD terminates
the requirements of this paragraph.
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Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations
New Requirements of This AD
Replacement
(h) Within 120 months after the effective
date of this AD, replace all midspar fuse pins
having part number (P/N) 311A1092–2 with
a midspar fuse pin having P/N 311A1092–3,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–54A1044, Revision 2, dated January 20,
2010. Accomplishing the requirements of this
paragraph terminates the requirements of
paragraph (g) of this AD for that fuse pin.
Actions Accomplished According to
Previous Revision of Service Information
(i) Actions done before the effective date of
this AD in accordance with Boeing Special
Attention Service Bulletin 737–54–1044,
Revision 1, dated November 26, 2008, are
acceptable for compliance with the
corresponding requirements of this AD.
WReier-Aviles on DSKGBLS3C1PROD with RULES
Alternative Methods of Compliance
(AMOCs)
(j)(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: Alan
Pohl, Aerospace Engineer, Airframe Branch,
ANM–120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6450; fax (425) 917–6590.
Information may be e-mailed to: 9-ANMSeattle-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) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that 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.
(4) AMOCs approved in accordance with
the requirements of AD 2008–21–03 are
acceptable for the corresponding
requirements of this AD.
Related Information
(k) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6450; fax (425)
917–6590; e-mail: alan.pohl@faa.gov.
Material Incorporated by Reference
(l) You must use Boeing Special Attention
Service Bulletin 737–54–1044, dated
December 10, 2007; or Boeing Alert Service
Bulletin 737–54A1044, Revision 2, dated
VerDate Mar<15>2010
15:20 Jan 04, 2011
Jkt 223001
January 20, 2010; 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
Boeing Alert Service Bulletin 737–54A1044,
Revision 2, dated January 20, 2010, under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Special Attention Service
Bulletin 737–54–1044, dated December 10,
2007, on November 13, 2008 (73 FR 59493,
October 9, 2008).
(3) 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.
(4) You may review copies of the service
information at the FAA, 1601 Lind Avenue,
SW., Renton, Washington. For information
on the availability of this material at the
FAA, call 425–227–1221.
(5) 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 an NARA facility, 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 22, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–33003 Filed 1–4–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
product. The MCAI describes the unsafe
condition as:
There have been two in-service reports of
main landing gear (MLG) tire failure on
landing, during which a flailing tire tread
caused damage to No. 2 and No. 3 hydraulic
system lines in the wing auxiliary spar area
on the left side of the aircraft. This damage
resulted in the loss of supply pressure to the
inboard and outboard brakes, as the only
remaining braking source available was the
No. 3 hydraulic system accumulator. The
degradation of the brake system performance
could adversely affect the aircraft during
landing.
*
*
*
*
*
The unsafe condition is loss of braking
capability, which could reduce the
ability of the flightcrew to safely land
the airplane. We are issuing this AD to
require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective
February 9, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 9, 2011.
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:
Christopher Alfano, Aerospace
Engineer, Airframe and Mechanical
Systems Branch, ANE–171, FAA, New
York Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7340; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
Discussion
[Docket No. FAA–2010–0959; Directorate
Identifier 2010–NM–119–AD; Amendment
39–16564; AD 2011–01–10]
AGENCY:
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 October 15, 2010 (75 FR
63420). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
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
There have been two in-service reports of
main landing gear (MLG) tire failure on
landing, during which a flailing tire tread
caused damage to No. 2 and No. 3 hydraulic
system lines in the wing auxiliary spar area
on the left side of the aircraft. This damage
resulted in the loss of supply pressure to the
inboard and outboard brakes, as the only
remaining braking source available was the
No. 3 hydraulic system accumulator. The
degradation of the brake system performance
could adversely affect the aircraft during
landing.
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Model BD–700–1A10 and BD–700–
1A11 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY:
PO 00000
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]]>Agencies
[Federal Register Volume 76, Number 3 (Wednesday, January 5, 2011)]
[Rules and Regulations]
[Pages 426-428]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-33003]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0855; Directorate Identifier 2010-NM-066-AD;
Amendment 39-16566; AD 2011-01-12]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-300, -400,
and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. That AD currently requires repetitive
inspections for discrepancies of the fuse pins of the inboard and
outboard midspar fittings of the nacelle strut, and corrective actions
if necessary. This new AD requires replacing the midspar fuse pins with
new, improved fuse pins, which would terminate the repetitive
inspections. This AD was prompted by a report of corrosion damage of
the chrome runout on the head side found on all four midspar fuse pins
of the nacelle strut. Additionally, a large portion of the chrome plate
was missing from the corroded area of the shank. We are issuing this AD
to prevent damage of the fuse pins of the inboard and outboard midspar
fittings of the nacelle strut, which could result in reduced structural
integrity of the fuse pins, and consequent loss of the strut and
separation of the engine from the airplane.
DATES: This AD is effective February 9, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 9,
2011.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 13, 2008 (73 FR 59493, October 9, 2008).
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. You may review copies of the
referenced 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.
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 (phone: 800-647-5527) is 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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6450; fax (425) 917-6590; e-mail: alan.pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness directive (AD) 2008-21-03, Amendment
39-15687 (73 FR 59493, October 9, 2008). That AD applies to the
specified products. The NPRM published in the Federal Register on
September 23, 2010 (75 FR 57882). That NPRM proposed to continue to
require repetitive inspections for discrepancies of the fuse pins of
the inboard and outboard midspar fittings of the nacelle strut, and
corrective actions if necessary. That NPRM also proposed to require
replacing the midspar fuse pins with new, improved fuse pins, which
would terminate the requirement for repetitive detailed inspections.
[[Page 427]]
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. Boeing supports the
NPRM.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
There are about 1,961 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 U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Repetitive detailed 4................ $85 None.................. $340, per 616 $209,440, per inspection
inspections (required by AD inspection cycle.
2008-21-03). cycle.
Midspar fuse pin replacement 1 per pin (up to 85 $843 per pin.......... Up to $3,712.... 616 Up to $2,286,592.
(new action). 4 pins per
airplane).
--------------------------------------------------------------------------------------------------------------------------------------------------------
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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
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 FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2008-21-03, Amendment 39-15687 (73 FR 59493, October 9, 2008), and
adding the following new AD:
2011-01-12 The Boeing Company: Amendment 39-16566; Docket No. FAA-
2010-0855; Directorate Identifier 2010-NM-066-AD.
Effective Date
(a) This airworthiness directive (AD) is effective February 9,
2011.
Affected ADs
(b) This AD supersedes AD 2008-21-03, Amendment 39-15687.
Applicability
(c) This AD applies to all The Boeing Company Model 737-300, -
400, and -500 series airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 54:
Nacelles/Pylons.
Unsafe Condition
(e) This AD results from a report of corrosion damage of the
chrome runout on the head side found on all four midspar fuse pins
of the nacelle strut. Additionally, a large portion of the chrome
plate was missing from the corroded area of the shank. The Federal
Aviation Administration is issuing this AD to prevent damage of the
fuse pins of the inboard and outboard midspar fittings of the
nacelle strut, which could result in reduced structural integrity of
the fuse pins, and consequent loss of the strut and separation of
the engine from 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 2008-21-03
Repetitive Inspections/Corrective Actions, With Revised Service
Information
(g) At the applicable time specified in paragraph 1.E.,
``Compliance'' of Boeing Special Attention Service Bulletin 737-54-
1044, dated December 10, 2007; except, where that service bulletin
specifies a compliance time after the date on that service bulletin,
this AD requires compliance within the specified compliance time
after November 13, 2008 (the effective date of AD 2008-21-03): Do a
detailed inspection for discrepancies of the fuse pins of the
inboard and outboard midspar fittings of the nacelle strut by doing
all the actions, including all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-54-1044, dated December 10, 2007; or
Boeing Alert Service Bulletin 737-54A1044, Revision 2, dated January
20, 2010. Do all applicable corrective actions before further
flight. Repeat the inspection at the time specified in paragraph
1.E. of Boeing Special Attention Service Bulletin 737-54-1044, dated
December 10, 2007. Accomplishing the actions of paragraph (h) of
this AD terminates the requirements of this paragraph.
[[Page 428]]
New Requirements of This AD
Replacement
(h) Within 120 months after the effective date of this AD,
replace all midspar fuse pins having part number (P/N) 311A1092-2
with a midspar fuse pin having P/N 311A1092-3, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-54A1044, Revision 2, dated January 20, 2010. Accomplishing the
requirements of this paragraph terminates the requirements of
paragraph (g) of this AD for that fuse pin.
Actions Accomplished According to Previous Revision of Service
Information
(i) Actions done before the effective date of this AD in
accordance with Boeing Special Attention Service Bulletin 737-54-
1044, Revision 1, dated November 26, 2008, are acceptable for
compliance with the corresponding requirements of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(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: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6450; fax (425)
917-6590. Information may be e-mailed 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) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that 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.
(4) AMOCs approved in accordance with the requirements of AD
2008-21-03 are acceptable for the corresponding requirements of this
AD.
Related Information
(k) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 917-6450; fax (425) 917-6590; e-mail:
alan.pohl@faa.gov.
Material Incorporated by Reference
(l) You must use Boeing Special Attention Service Bulletin 737-
54-1044, dated December 10, 2007; or Boeing Alert Service Bulletin
737-54A1044, Revision 2, dated January 20, 2010; 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 Boeing Alert Service Bulletin 737-
54A1044, Revision 2, dated January 20, 2010, under 5 U.S.C. 552(a)
and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Boeing Special Attention Service
Bulletin 737-54-1044, dated December 10, 2007, on November 13, 2008
(73 FR 59493, October 9, 2008).
(3) 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.
(4) You may review copies of the service information at the FAA,
1601 Lind Avenue, SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
(5) 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 an NARA facility, 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 22, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-33003 Filed 1-4-11; 8:45 am]
BILLING CODE 4910-13-P
