AD 2011-23-05
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Boeing | 737-300 | Airworthiness Directives; The Boeing Company Model 737-300, -400, and -500 Series Airplanes |
Unsafe Condition
Cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringers S-20 and S-21, on both the left and right sides of the airplane. 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.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringers S-20 and S-21, on both the left and right sides of the airplane. Repair any identified cracking in accordance with an approved method or using data that meet the certification basis of the airplane, approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA).
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 4,500 flight cycles after accomplishment of the most recent Part 2 or Part 4 inspection, with a grace period of 90 days. For certain airplanes with 40,000 or more total flight cycles and solid fuselage skins, the compliance time for Part 2 inspection is extended to 90 days.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
The Boeing Company Model 737-300, -400, and -500 series airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
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.
Applicability Source Text
Show captured applicability text from the source AD
(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.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 76, Number 211 (Tuesday, November 1, 2011)]
[Rules and Regulations]
[Pages 67343-67346]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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:
<bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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 <a href="/cdn-cgi/l/email-protection#0469612a666b61676b6944666b616d6a632a676b69"><span class="__cf_email__" data-cfemail="5538307b373a30363a3815373a303c3b327b363a38">[email protected]</span></a>;
Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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: <a href="/cdn-cgi/l/email-protection#fc8b9d859299d290939f97998888bc9a9d9dd29b938a"><span class="__cf_email__" data-cfemail="512630283f347f3d3e323a342525113730307f363e27">[email protected]</span></a>.
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:
<bullet> In accordance with a method that we approve; or
<bullet> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>, 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: <a href="/cdn-cgi/l/email-protection#784155393635552b1d190c0c141d55393b37553935373b552a1d090d1d0b0c0b381e1919561f170e"><span class="__cf_email__" data-cfemail="b98094f8f7f494eadcd8cdcdd5dc94f8faf694f8f4f6fa94ebdcc8ccdccacdcaf9dfd8d897ded6cf">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#5423352d3a317a383b373f312020143235357a333b22"><span class="__cf_email__" data-cfemail="90e7f1e9fef5befcfff3fbf5e4e4d0f6f1f1bef7ffe6">[email protected]</span></a>.
(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
<a href="/cdn-cgi/l/email-protection#a9c4cc87cbc6cccac6c4e9cbc6ccc0c7ce87cac6c4"><span class="__cf_email__" data-cfemail="aac7cf84c8c5cfc9c5c7eac8c5cfc3c4cd84c9c5c7">[email protected]</span></a>; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(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 <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.
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
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2025-02-02 Recurring
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: cracks in the frame inner chord and web at station (STA) 727 between S-11L and S-13L, which could result in the inability of a principal structural element to sustain limit load, and adversely affe...
2024-23-03
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: Failure of the spoiler deflection to engage the cruise thrust split monitor (MONFD) used by the autothrottle (A/T) system, which could lead to significant throttle split, leading to asymmetric thru...
2024-18-08
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: The protective spiral wrap used on certain galley wire bundles does not have the correct flammability properties and may not self-extinguish.
2023-13-12 Recurring
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: premature aging of certain passenger chemical oxygen generators, which could fail to deliver oxygen during an emergency, possibly resulting in injury to the airplane occupants.