Airworthiness Directives; The Boeing Company Model 737-300, -400, and -500 Series Airplanes, 67343-67346 [2011-28053]
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Federal Register / Vol. 76, No. 211 / Tuesday, November 1, 2011 / Rules and Regulations
Services, 65921 Tarbes Cedex 9, France;
telephone: +33 (0)5 62 41 73 00; fax: +33 (0)5
62 41 7654; or in the United States contact
SOCATA North America, Inc., North Perry
Airport, 7501 South Airport Road, Pembroke
Pines, Florida 33023; telephone: (954) 893–
1400; fax: (954) 964–4141; Internet: https://
www.socatanorthamerica.com.
(3) You may review copies of the
referenced service information at the FAA,
Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
(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 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 Kansas City, Missouri, on
October 24, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2011–27949 Filed 10–31–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1162; Directorate
Identifier 2011–NM–186–AD; Amendment
39–16856; AD 2011–23–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–300, –400, and
–500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain Model 737–300, –400, and –500
series airplanes. That AD currently
requires repetitive inspections for
cracking of the 1.04-inch nominal
diameter wire penetration hole, and
applicable related investigative and
corrective actions. This AD reduces the
compliance times for those actions. This
AD was prompted by reports of cracking
in the frame, or in the frame and frame
reinforcement, common to the 1.04-inch
nominal diameter wire penetration hole
intended for wire routing; and recent
reports of multiple adjacent frame
cracking found before the compliance
time required by the existing AD. Such
cracking could reduce the structural
capability of the frames to sustain limit
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SUMMARY:
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loads, and result in cracking in the
fuselage skin and subsequent rapid
depressurization of the airplane. We are
issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective November
16, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 16, 2011.
We must receive any comments on
this AD by December 16, 2011.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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; email
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 street address for
the Docket Office (phone: (800) 647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425)
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67343
917–6447; fax: (425) 917–6590; email:
wayne.lockett@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 26, 2009, we issued AD
2009–02–06 R1, Amendment 39–16015
(74 FR 45979, September 8, 2009), for
certain Model 737–300, –400, and –500
series airplanes. That AD requires
repetitive inspections for cracking of the
1.04-inch nominal diameter wire
penetration hole in the frame and in the
frame reinforcement, between stringers
S–20 and S–21, on both the left and
right sides of the airplane, and
applicable related investigative and
corrective actions. That AD resulted
from reports of cracking in the frame, or
in the frame and frame reinforcement,
common to the 1.04-inch nominal
diameter wire penetration hole intended
for wire routing. We issued that AD to
detect and correct cracking in the
fuselage frames and frame
reinforcements, which could reduce the
structural capability of the frames to
sustain limit loads, and result in
cracking in the fuselage skin and
subsequent rapid depressurization of
the airplane.
Actions Since AD Was Issued
Since we issued AD 2009–02–06 R1,
Amendment 39–16015 (74 FR 45979,
September 8, 2009), we received a
report of four adjacent cracked frames at
body station (BS) 500B, BS 500C, BS
500D, and BS 520 in the forward cargo
compartment between S–20L and S–21L
on a Model 737–300 series airplane. The
cracks at BS 500B and BS 500C were
completely through the frame and failsafe chord. The BS 500B frame was also
cracked on the right-hand side. The
cracks were discovered when the
airplane had accumulated 44,535 total
flight cycles and 44,876 total flight
hours—before the compliance time
required by AD 2009–02–06 R1.
Relevant Service Information
AD 2009–02–06 R1, Amendment 39–
16015 (74 FR 45979, September 8,
2009), referred to Boeing Alert Service
Bulletin 737–53A1279, dated December
18, 2007, as the appropriate source of
service information for the required
actions. Boeing has since revised this
service bulletin. We reviewed Boeing
Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011,
which shortens the compliance time to
30,000 total flight cycles, with a grace
period of 30 or 90 days, and reduces the
repetitive interval from 14,000 to 4,500
flight cycles. The procedures are
unchanged from those specified in
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Federal Register / Vol. 76, No. 211 / Tuesday, November 1, 2011 / Rules and Regulations
Boeing Alert Service Bulletin 737–
53A1279, dated December 18, 2007.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
AD Requirements
This AD requires accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between the AD and the Service
Information.’’
Differences Between the AD and the
Service Information
Boeing Alert Service Bulletin 737–
53A1279, Revision 1, dated September
2, 2011, specifies to contact the
manufacturer for instructions on how to
repair certain conditions, but this
proposed AD would require repairing
those conditions in one of the following
ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Boeing Alert Service Bulletin 737–
53A1279, Revision 1, dated September
2, 2011, specifies compliance with the
Part 4 inspection by the later of 4,500
flight cycles or 90 days—both after the
date on this service bulletin. In some
cases, this compliance time might occur
before the Part 2 inspection. This AD (in
paragraph (h)) therefore requires the
Part 4 inspection within 4,500 flight
cycles after accomplishment of the most
recent Part 2 or Part 4 inspection, with
a grace period of 90 days. We have
coordinated this difference with Boeing.
For certain airplanes that have
accumulated 40,000 or more total flight
cycles, Boeing Alert Service Bulletin
737–53A1279, Revision 1, dated
September 2, 2011, specifies a 30-day
compliance time for the Part 2
inspection. Paragraph (k)(2) of this AD
extends that compliance time to 90 days
for those airplanes, if the original chem.milled fuselage skins have been
replaced with solid skins. This
difference has been coordinated with
Boeing.
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because cracking in multiple
adjacent fuselage frames and frame
reinforcements reduces the structural
capability of the frames to sustain limit
loads, and result in cracking in the
fuselage skin and subsequent rapid
depressurization of the airplane.
Therefore, we find that notice and
opportunity for prior public comment
are impracticable and that good cause
exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the Docket No. FAA–
2011–1162 and directorate identifier
2011–NM–186–AD at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD affects 605
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Inspection ..............
16 work-hours × $85 per hour =
$1,360 per inspection cycle.
None ........
$1,360 per inspection cycle ................
We estimate the following costs to do
any necessary related investigative
actions that would be required based on
the results of the HFEC inspections. We
have no way of determining the number
Cost on U.S. operators
$822,800 per inspection
cycle.
of aircraft that might need this
inspection:
ON-CONDITION COSTS
Labor cost
Parts cost
On-condition inspection .......................
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Action
2 work-hours × $85 per hour = $170 ..............................................................
None ........
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition repair or
optional modification specified in this
AD.
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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
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Cost per
product
$170
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
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Federal Register / Vol. 76, No. 211 / Tuesday, November 1, 2011 / Rules and Regulations
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
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (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 FAA amends § 39.13 by
removing airworthiness directive (AD)
2009–02–06 R1, Amendment 39–16015
(74 FR 45979, September 8, 2009), and
adding the following new AD:
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■
2011–23–05 The Boeing Company:
Amendment 39–16856; Docket No.
FAA–2011–1162; Directorate Identifier
2011–NM–186–AD.
(a) Effective Date
This AD is effective November 16, 2011.
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(b) Affected ADs
This AD supersedes AD 2009–02–06 R1,
Amendment 39–16015 (74 FR 45979,
September 8, 2009).
(c) Applicability
This AD applies to The Boeing Company
Model 737–300, –400, –500 series airplanes,
certificated in any category; as identified in
Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of four
cracked frames at certain body stations (BS)
in the forward cargo compartment. We are
issuing this AD to detect and correct cracking
in the fuselage frames and frame
reinforcements, which could reduce the
structural capability of the frames to sustain
limit loads, and result in cracking in the
fuselage skin and subsequent rapid
depressurization of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011, except
as required by paragraphs (k)(1), (k)(2), and
(k)(4) of this AD: Do a high frequency eddy
current (HFEC) surface or HFEC hole/edge
inspection for any cracking of the 1.04-inch
nominal diameter wire penetration hole in
the frame and frame reinforcement between
stringer S–20 and S–21, in accordance with
Part 2 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011.
(h) Repetitive Inspection
Within 4,500 flight cycles after
accomplishment of the most recent
inspection specified in Part 2 or Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 1,
dated September 2, 2011, or within 90 days
after the effective date of this AD, whichever
occurs later: Do an HFEC hole/edge
inspection for cracking of the 1.04-inch
nominal diameter wire penetration hole in
the frame and frame reinforcement between
S–20 and S–21, in accordance with Part 4 of
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011. Repeat
the inspection thereafter at intervals not to
exceed 4,500 flight cycles.
(i) Repair
If any cracking is found during any
inspection required by paragraph (g) or (h) of
this AD: Before further flight, repair the crack
including doing all related investigative and
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1279,
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67345
Revision 1, dated September 2, 2011, except
as required by paragraph (k)(3) of this AD.
All related investigative and applicable
corrective actions must be done before
further flight. Accomplishment of the
requirements of this paragraph terminates the
repetitive inspection requirements of
paragraph (h) of this AD for the repaired
location of that frame.
(j) Optional Terminating Action
Accomplishment of the preventive
modification, including doing all related
investigative and applicable corrective
actions, specified in Part 5 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1279, Revision 1,
dated September 2, 2011, except as required
by paragraph (k)(3) of this AD, terminates the
repetitive inspection requirements of
paragraph (h) of this AD for the modified
location of that frame, provided the
modification is done before further flight
after an inspection required by paragraph (g)
or (h) of this AD has been done, and no
cracking was found on that frame location
during that inspection.
(k) Exceptions to Service Bulletin
Specifications
The following exceptions apply in this AD.
(1) Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011, refers
to a compliance time ‘‘from date on Revision
1 of this service bulletin,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(2) For airplanes meeting all of the criteria
specified in paragraphs (k)(2)(i), (k)(2)(ii),
and (k)(2)(iii) of this AD: The compliance
time for the initial inspection specified in
Part 2 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1279,
Revision 1, dated September 2, 2011, and
required by paragraph (g) of this AD, may be
extended to 90 days after the effective date
of this AD.
(i) Model 737–300 series airplanes in
Group 1, line numbers 1001 through 2565
inclusive;
(ii) Airplanes that have accumulated
40,000 or more total flight cycles as of the
effective date of this AD; and
(iii) Airplanes on which the modification
specified in Boeing Service Bulletin 737–53–
1273, dated September 20, 2006; Revision 1,
dated December 21, 2006; Revision 2, dated
June 4, 2007; Revision 3, dated December 7,
2009; or Revision 4, dated July 23, 2010; has
been done, including any configuration or
deviation that has been approved as an
AMOC during accomplishment of these
service bulletins, by the Boeing Commercial
Airplanes Organization Designation
Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft
Certification Office (ACO) to make those
findings.
(3) Where Boeing Alert Service Bulletin
737–53A1279, Revision 1, dated September
2, 2011 specifies to contact Boeing for
appropriate repair instructions: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (m) of this AD.
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Federal Register / Vol. 76, No. 211 / Tuesday, November 1, 2011 / Rules and Regulations
(4) The ‘‘Condition’’ column of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1279, Revision 1, dated
September 2, 2011, refers to total flight
cycles, ‘‘at the date of/on this service
bulletin.’’ However, this AD applies to the
airplanes with the specified total flight cycles
as of the effective date of this AD.
(l) Credit for Actions Accomplished in
Accordance With Previous Service
Information
Actions done in accordance with Boeing
Alert Service Bulletin 737–53A1279, dated
December 18, 2007, before the effective date
of this AD are acceptable for compliance with
the corresponding actions required by
paragraphs (g), (h), (i), and (j) of this AD.
(m) Alternative Methods of Compliance
(AMOCs)
(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. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by
Boeing Commercial Airplanes 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 for paragraphs (h)
and (i) of AD 2009–02–06 R1, Amendment
39–16015 (74 FR 45979, September 8, 2009),
are approved as AMOCs for the
corresponding provisions of paragraphs (g),
(h), and (i) of this AD.
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(n) Related Information
For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle ACO,
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425) 917–
6447; fax: (425) 917–6590; email:
wayne.lockett@faa.gov.
(o) Material Incorporated by Reference
(1) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference (IBR) under 5
U.S.C. 552(a) and 1 CFR part 51 of the
following service information on the date
specified:
(i) Boeing Alert Service Bulletin 737–
53A1279, Revision 1, dated September 2,
2011, approved for IBR November 16, 2011.
(2) If you accomplish the optional actions
specified by this AD, you must use the
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Jkt 226001
following service information to perform
those actions, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference (IBR) of the following service
information on the date specified:
(i) Boeing Alert Service Bulletin 737–
53A1279, Revision 1, dated September 2,
2011, approved for IBR November 16, 2011.
(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 October
20, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–28053 Filed 10–31–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1161; Directorate
Identifier 2011–CE–036–AD; Amendment
39–16850; AD 2011–21–51]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
Examining the AD Docket
We are adopting a new
airworthiness directive (AD) for certain
Cessna Aircraft Company (Cessna)
Model 525C airplanes. This emergency
AD was sent previously to all known
U.S. owners and operators of these
airplanes. This AD requires replacing
certain lithium-ion batteries installed as
the main aircraft battery with either a
Ni-Cad or a lead acid battery. This AD
was prompted by a report of a battery
fire that resulted after an energized
SUMMARY:
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ground power unit was connected to
one of the affected airplanes equipped
with a lithium-ion battery as the main
aircraft battery. We are issuing this AD
to correct the unsafe condition on these
products.
DATES: This AD is effective November 1,
2011 to all persons except those persons
to whom it was made immediately
effective by Emergency AD 2011–21–51,
issued on October 6, 2011, which
contained the requirements of this
amendment.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication identified in the
AD as of November 1, 2011.
We must receive comments on this
AD by December 16, 2011.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact Cessna Aircraft
Company, Product Support, P.O. Box
7706, Wichita, KS 67277; telephone:
(316) 517–6000; fax: (316) 517–8500;
email:
Customercare@cessna.textron.com;
Internet: https://www.cessna.com. You
may review copies of the referenced
service information at the FAA, Small
Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–
4148.
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations Office 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 street address for
the Docket Operations Office (phone:
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Richard Rejniak, Aerospace Engineer,
E:\FR\FM\01NOR1.SGM
01NOR1
]]>Agencies
[Federal Register Volume 76, Number 211 (Tuesday, November 1, 2011)]
[Rules and Regulations]
[Pages 67343-67346]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-28053]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1162; Directorate Identifier 2011-NM-186-AD;
Amendment 39-16856; AD 2011-23-05]
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; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain Model 737-300, -400, and -500 series airplanes. That AD
currently requires repetitive inspections for cracking of the 1.04-inch
nominal diameter wire penetration hole, and applicable related
investigative and corrective actions. This AD reduces the compliance
times for those actions. This AD was prompted by reports of cracking in
the frame, or in the frame and frame reinforcement, common to the 1.04-
inch nominal diameter wire penetration hole intended for wire routing;
and recent reports of multiple adjacent frame cracking found before the
compliance time required by the existing AD. Such cracking could reduce
the structural capability of the frames to sustain limit loads, and
result in cracking in the fuselage skin and subsequent rapid
depressurization of the airplane. We are issuing this AD to correct the
unsafe condition on these products.
DATES: This AD is effective November 16, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 16,
2011.
We must receive any comments on this AD by December 16, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
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; email 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 street address for
the Docket Office (phone: (800) 647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO),
FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425)
917-6447; fax: (425) 917-6590; email: wayne.lockett@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 26, 2009, we issued AD 2009-02-06 R1, Amendment 39-16015
(74 FR 45979, September 8, 2009), for certain Model 737-300, -400, and
-500 series airplanes. That AD requires repetitive inspections for
cracking of the 1.04-inch nominal diameter wire penetration hole in the
frame and in the frame reinforcement, between stringers S-20 and S-21,
on both the left and right sides of the airplane, and applicable
related investigative and corrective actions. That AD resulted from
reports of cracking in the frame, or in the frame and frame
reinforcement, common to the 1.04-inch nominal diameter wire
penetration hole intended for wire routing. We issued that AD to detect
and correct cracking in the fuselage frames and frame reinforcements,
which could reduce the structural capability of the frames to sustain
limit loads, and result in cracking in the fuselage skin and subsequent
rapid depressurization of the airplane.
Actions Since AD Was Issued
Since we issued AD 2009-02-06 R1, Amendment 39-16015 (74 FR 45979,
September 8, 2009), we received a report of four adjacent cracked
frames at body station (BS) 500B, BS 500C, BS 500D, and BS 520 in the
forward cargo compartment between S-20L and S-21L on a Model 737-300
series airplane. The cracks at BS 500B and BS 500C were completely
through the frame and fail-safe chord. The BS 500B frame was also
cracked on the right-hand side. The cracks were discovered when the
airplane had accumulated 44,535 total flight cycles and 44,876 total
flight hours--before the compliance time required by AD 2009-02-06 R1.
Relevant Service Information
AD 2009-02-06 R1, Amendment 39-16015 (74 FR 45979, September 8,
2009), referred to Boeing Alert Service Bulletin 737-53A1279, dated
December 18, 2007, as the appropriate source of service information for
the required actions. Boeing has since revised this service bulletin.
We reviewed Boeing Alert Service Bulletin 737-53A1279, Revision 1,
dated September 2, 2011, which shortens the compliance time to 30,000
total flight cycles, with a grace period of 30 or 90 days, and reduces
the repetitive interval from 14,000 to 4,500 flight cycles. The
procedures are unchanged from those specified in
[[Page 67344]]
Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the AD and the Service Information.''
Differences Between the AD and the Service Information
Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011, specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011, specifies compliance with the Part 4 inspection by
the later of 4,500 flight cycles or 90 days--both after the date on
this service bulletin. In some cases, this compliance time might occur
before the Part 2 inspection. This AD (in paragraph (h)) therefore
requires the Part 4 inspection within 4,500 flight cycles after
accomplishment of the most recent Part 2 or Part 4 inspection, with a
grace period of 90 days. We have coordinated this difference with
Boeing.
For certain airplanes that have accumulated 40,000 or more total
flight cycles, Boeing Alert Service Bulletin 737-53A1279, Revision 1,
dated September 2, 2011, specifies a 30-day compliance time for the
Part 2 inspection. Paragraph (k)(2) of this AD extends that compliance
time to 90 days for those airplanes, if the original chem.-milled
fuselage skins have been replaced with solid skins. This difference has
been coordinated with Boeing.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
cracking in multiple adjacent fuselage frames and frame reinforcements
reduces the structural capability of the frames to sustain limit loads,
and result in cracking in the fuselage skin and subsequent rapid
depressurization of the airplane. Therefore, we find that notice and
opportunity for prior public comment are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the Docket No. FAA-2011-1162 and directorate identifier 2011-NM-186-AD
at the beginning of your comments. We specifically invite comments on
the overall regulatory, economic, environmental, and energy aspects of
this AD. We will consider all comments received by the closing date and
may amend this AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 605 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection........................ 16 work-hours x $85 per None............... $1,360 per inspection $822,800 per inspection cycle.
hour = $1,360 per cycle.
inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary related
investigative actions that would be required based on the results of
the HFEC inspections. We have no way of determining the number of
aircraft that might need this inspection:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
On-condition inspection................. 2 work-hours x $85 per hour = None.................... $170
$170.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to
provide a cost estimate for the on-condition repair or optional
modification specified in this AD.
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
[[Page 67345]]
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
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
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends part 39 of the Federal Aviation
Regulations (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)
2009-02-06 R1, Amendment 39-16015 (74 FR 45979, September 8, 2009), and
adding the following new AD:
2011-23-05 The Boeing Company: Amendment 39-16856; Docket No. FAA-
2011-1162; Directorate Identifier 2011-NM-186-AD.
(a) Effective Date
This AD is effective November 16, 2011.
(b) Affected ADs
This AD supersedes AD 2009-02-06 R1, Amendment 39-16015 (74 FR
45979, September 8, 2009).
(c) Applicability
This AD applies to The Boeing Company Model 737-300, -400, -500
series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of four cracked frames at
certain body stations (BS) in the forward cargo compartment. We are
issuing this AD to detect and correct cracking in the fuselage
frames and frame reinforcements, which could reduce the structural
capability of the frames to sustain limit loads, and result in
cracking in the fuselage skin and subsequent rapid depressurization
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279,
Revision 1, dated September 2, 2011, except as required by
paragraphs (k)(1), (k)(2), and (k)(4) of this AD: Do a high
frequency eddy current (HFEC) surface or HFEC hole/edge inspection
for any cracking of the 1.04-inch nominal diameter wire penetration
hole in the frame and frame reinforcement between stringer S-20 and
S-21, in accordance with Part 2 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011.
(h) Repetitive Inspection
Within 4,500 flight cycles after accomplishment of the most
recent inspection specified in Part 2 or Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1279, Revision 1, dated September 2, 2011, or within 90 days
after the effective date of this AD, whichever occurs later: Do an
HFEC hole/edge inspection for cracking of the 1.04-inch nominal
diameter wire penetration hole in the frame and frame reinforcement
between S-20 and S-21, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1279, Revision 1, dated September 2, 2011. Repeat the inspection
thereafter at intervals not to exceed 4,500 flight cycles.
(i) Repair
If any cracking is found during any inspection required by
paragraph (g) or (h) of this AD: Before further flight, repair the
crack including doing all related investigative and applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision
1, dated September 2, 2011, except as required by paragraph (k)(3)
of this AD. All related investigative and applicable corrective
actions must be done before further flight. Accomplishment of the
requirements of this paragraph terminates the repetitive inspection
requirements of paragraph (h) of this AD for the repaired location
of that frame.
(j) Optional Terminating Action
Accomplishment of the preventive modification, including doing
all related investigative and applicable corrective actions,
specified in Part 5 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1279, Revision 1, dated September 2,
2011, except as required by paragraph (k)(3) of this AD, terminates
the repetitive inspection requirements of paragraph (h) of this AD
for the modified location of that frame, provided the modification
is done before further flight after an inspection required by
paragraph (g) or (h) of this AD has been done, and no cracking was
found on that frame location during that inspection.
(k) Exceptions to Service Bulletin Specifications
The following exceptions apply in this AD.
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011,
refers to a compliance time ``from date on Revision 1 of this
service bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) For airplanes meeting all of the criteria specified in
paragraphs (k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD: The
compliance time for the initial inspection specified in Part 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1279, Revision 1, dated September 2, 2011, and required by
paragraph (g) of this AD, may be extended to 90 days after the
effective date of this AD.
(i) Model 737-300 series airplanes in Group 1, line numbers 1001
through 2565 inclusive;
(ii) Airplanes that have accumulated 40,000 or more total flight
cycles as of the effective date of this AD; and
(iii) Airplanes on which the modification specified in Boeing
Service Bulletin 737-53-1273, dated September 20, 2006; Revision 1,
dated December 21, 2006; Revision 2, dated June 4, 2007; Revision 3,
dated December 7, 2009; or Revision 4, dated July 23, 2010; has been
done, including any configuration or deviation that has been
approved as an AMOC during accomplishment of these service
bulletins, by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle Aircraft Certification Office (ACO) to make those
findings.
(3) Where Boeing Alert Service Bulletin 737-53A1279, Revision 1,
dated September 2, 2011 specifies to contact Boeing for appropriate
repair instructions: Before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (m) of this AD.
[[Page 67346]]
(4) The ``Condition'' column of paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011, refers to total flight cycles, ``at the date of/
on this service bulletin.'' However, this AD applies to the
airplanes with the specified total flight cycles as of the effective
date of this AD.
(l) Credit for Actions Accomplished in Accordance With Previous Service
Information
Actions done in accordance with Boeing Alert Service Bulletin
737-53A1279, dated December 18, 2007, before the effective date of
this AD are acceptable for compliance with the corresponding actions
required by paragraphs (g), (h), (i), and (j) of this AD.
(m) Alternative Methods of Compliance (AMOCs)
(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. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, send it to the attention of the person identified in the
Related Information section of this AD. Information may be emailed
to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by Boeing
Commercial Airplanes 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 for paragraphs (h) and (i) of AD 2009-02-06
R1, Amendment 39-16015 (74 FR 45979, September 8, 2009), are
approved as AMOCs for the corresponding provisions of paragraphs
(g), (h), and (i) of this AD.
(n) Related Information
For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle ACO, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425)
917-6447; fax: (425) 917-6590; email: wayne.lockett@faa.gov.
(o) Material Incorporated by Reference
(1) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the
following service information on the date specified:
(i) Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011, approved for IBR November 16, 2011.
(2) If you accomplish the optional actions specified by this AD,
you must use the following service information to perform those
actions, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference (IBR) of
the following service information on the date specified:
(i) Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated
September 2, 2011, approved for IBR November 16, 2011.
(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 October 20, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-28053 Filed 10-31-11; 8:45 am]
BILLING CODE 4910-13-P
