80 FR 15523 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 56 (March 24, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 56 (March 24, 2015)
| Page Range | 15523-15525 | |
| FR Document | 2015-06574 |
[Federal Register Volume 80, Number 56 (Tuesday, March 24, 2015)] [Proposed Rules] [Pages 15523-15525] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-06574] [[Page 15523]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0495; Directorate Identifier 2014-NM-172-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This proposed AD was prompted by reports of cracking at certain fastener locations in the window corners of the window belt area. This proposed AD would require repetitive high frequency eddy current (HFEC) inspections for fatigue cracking in certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions if necessary. This proposed AD would also provide an optional preventive modification that would terminate the repetitive inspections at the modified location. We are proposing this AD to detect and correct fatigue cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane. DATES: We must receive comments on this proposed AD by May 8, 2015. 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 http://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 proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0495. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0495; 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 proposed 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: Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6573; fax: 425-917-6590; email: haytham.alaidy@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0495; Directorate Identifier 2014-NM-172-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of cracking at certain fastener locations in the window corners of the window belt. At the time of the crack detection, the airplanes had accumulated between 37,842 and 49,050 total flight cycles. Fatigue cracking of the fastener locations in the window corners of the window belt area between station (STA) 360 and STA 540 and between STA 727 and STA 908, left-side and right-side of the fuselage, at and between stringers S-11 and S-13, if not corrected, could result in cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane. Related Service Information We reviewed Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. The service information describes procedures for inspections, preventative modification, and repairs of the window corners. Refer to this service information for information on the procedures and compliance times. This service information is reasonably available; see ADDRESSES for ways to access this service information. FAA's Determination We are proposing 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. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information identified previously. The phrase ``related investigative actions'' is used in this proposed AD. ``Related investigative actions'' are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. ``Corrective actions'' are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Explanation of ``RC'' Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service [[Page 15524]] information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as RC (required for compliance) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. Steps that are identified as RC in any service information must be done to comply with the proposed AD. However, steps that are not identified as RC are recommended. Those steps that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an alternative method of compliance (AMOC), provided the steps identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps identified as RC will require approval of an AMOC. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, 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. Costs of Compliance We estimate that this proposed AD affects 142 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs: Required Actions -------------------------------------------------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Inspection............................. Up to 2,312 work-hours $0 Up to $196,520 per inspection cycle Up to $27,905,840 per inspection x $85 per hour = cycle. $196,520 per inspection cycle. -------------------------------------------------------------------------------------------------------------------------------------------------------- Estimated Costs: Optional Actions ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Preventive modification............... 108 work-hours x $85 $0 $9,180. per hour = $9,180. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Repair................................ Up to 18 work-hours x $0 Up to $1,530 per repair. $85 per hour = $1,530 per repair. ---------------------------------------------------------------------------------------------------------------- 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 determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 adding the following new airworthiness directive (AD): [[Page 15525]] The Boeing Company: Docket No. FAA-2015-0495; Directorate Identifier 2014-NM-172-AD. (a) Comments Due Date We must receive comments by May 8, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 737-300, -400, and - 500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking at certain fastener locations in the window corners of the window belt area. We are issuing this AD to detect and correct fatigue cracking around the fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections At the applicable time specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, except as required by paragraph (i)(1) of this AD: Do external surface high frequency eddy current (HFEC) inspections for cracking of the skin at the 12 fastener locations at the upper forward and lower aft corners of each window between station (STA) 360 and STA 540 and between STA 727 and STA 908, left- side and right-side of the fuselage, at and between stringers S-11 and S-13, and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, until the terminating action specified in paragraph (h) of this AD is done. (h) Optional Preventive Modification Accomplishment of a preventive modification in the fastener locations in the window corners of the window belt area between station (STA) 360 and STA 540 and between STA 727 and STA 908, left- side and right-side fuselage, at and between stringers S-11 and S- 13, terminates the inspections required by paragraph (g) of this AD at the modified location only. The modification, including all applicable related investigative and corrective actions, must be done in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, except as required by paragraph (i)(2) of this AD. (i) Exceptions to the Service Bulletin Specifications (1) Where Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (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. 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 paragraph (k)(1) 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) If any service information contains steps that are identified as RC (Required for Compliance), those steps must be done to comply with this AD; any steps that are not identified as RC are recommended. Those steps that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the steps identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps identified as RC require approval of an AMOC. (4) 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. (k) Related Information (1) For more information about this AD, contact Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6447; fax: 425-917-6590; email: haytham.alaidy@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on March 13, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-06574 Filed 3-23-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 56 / Tuesday, March 24, 2015 / Proposed Rules 15523
DEPARTMENT OF TRANSPORTATION www.myboeingfleet.com. You may view 37,842 and 49,050 total flight cycles.
this referenced service information at Fatigue cracking of the fastener
Federal Aviation Administration the FAA, Transport Airplane locations in the window corners of the
Directorate, 1601 Lind Avenue SW., window belt area between station (STA)
14 CFR Part 39 Renton, WA. For information on the 360 and STA 540 and between STA 727
[Docket No. FAA–2015–0495; Directorate availability of this material at the FAA, and STA 908, left-side and right-side of
Identifier 2014–NM–172–AD] call 425–227–1221. It is also available the fuselage, at and between stringers
on the Internet at http:// S–11 and S–13, if not corrected, could
RIN 2120–AA64 www.regulations.gov by searching for result in cracking around fastener
and locating Docket No. FAA–2015– locations that could cause multiple
Airworthiness Directives; The Boeing 0495. window corner skin cracks, which
Company Airplanes
Examining the AD Docket could result in rapid decompression and
AGENCY: Federal Aviation loss of structural integrity of the
Administration (FAA), DOT. You may examine the AD docket on airplane.
the Internet at http://
ACTION: Notice of proposed rulemaking Related Service Information
www.regulations.gov by searching for
(NPRM).
and locating Docket No. FAA–2015– We reviewed Boeing Alert Service
SUMMARY: We propose to adopt a new 0495; or in person at the Docket Bulletin 737–53A1328, dated July 22,
airworthiness directive (AD) for certain Management Facility between 9 a.m. 2014. The service information describes
The Boeing Company Model 737–300, and 5 p.m., Monday through Friday, procedures for inspections, preventative
–400, and –500 series airplanes. This except Federal holidays. The AD docket modification, and repairs of the window
proposed AD was prompted by reports contains this proposed AD, the corners. Refer to this service
of cracking at certain fastener locations regulatory evaluation, any comments information for information on the
in the window corners of the window received, and other information. The procedures and compliance times. This
belt area. This proposed AD would street address for the Docket Office service information is reasonably
require repetitive high frequency eddy (phone: 800–647–5527) is in the available; see ADDRESSES for ways to
current (HFEC) inspections for fatigue ADDRESSES section. Comments will be access this service information.
cracking in certain fastener locations in available in the AD docket shortly after
receipt. FAA’s Determination
the window corners of the window belt
area, and related investigative and FOR FURTHER INFORMATION CONTACT: We are proposing this AD because we
corrective actions if necessary. This Haytham Alaidy, Aerospace Engineer, evaluated all the relevant information
proposed AD would also provide an Airframe Branch, ANM–120S, FAA, and determined the unsafe condition
optional preventive modification that Seattle Aircraft Certification Office described previously is likely to exist or
would terminate the repetitive (ACO), 1601 Lind Avenue SW., Renton, develop in other products of the same
inspections at the modified location. We WA 98057–3356; phone: 425–917–6573; type design.
are proposing this AD to detect and fax: 425–917–6590; email:
haytham.alaidy@faa.gov. Proposed AD Requirements
correct fatigue cracking around fastener
locations that could cause multiple SUPPLEMENTARY INFORMATION: This proposed AD would require
window corner skin cracks, which accomplishing the actions specified in
Comments Invited the service information identified
could result in rapid decompression and
loss of structural integrity of the We invite you to send any written previously.
relevant data, views, or arguments about The phrase ‘‘related investigative
airplane.
this proposal. Send your comments to actions’’ is used in this proposed AD.
DATES: We must receive comments on an address listed under the ADDRESSES ‘‘Related investigative actions’’ are
this proposed AD by May 8, 2015. section. Include ‘‘Docket No. FAA– follow-on actions that (1) are related to
ADDRESSES: You may send comments, 2015–0495; Directorate Identifier 2014– the primary actions, and (2) further
using the procedures found in 14 CFR NM–172–AD’’ at the beginning of your investigate the nature of any condition
11.43 and 11.45, by any of the following comments. We specifically invite found. Related investigative actions in
methods: comments on the overall regulatory, an AD could include, for example,
• Federal eRulemaking Portal: Go to economic, environmental, and energy inspections.
http://www.regulations.gov. Follow the aspects of this proposed AD. We will The phrase ‘‘corrective actions’’ is
instructions for submitting comments. consider all comments received by the used in this proposed AD. ‘‘Corrective
• Fax: 202–493–2251. closing date and may amend this actions’’ are actions that correct or
• Mail: U.S. Department of proposed AD because of those address any condition found. Corrective
Transportation, Docket Operations, M– comments. actions in an AD could include, for
30, West Building Ground Floor, Room We will post all comments we example, repairs.
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http://
Washington, DC 20590. Explanation of ‘‘RC’’ Steps in Service
www.regulations.gov, including any
• Hand Delivery: Deliver to Mail Information
personal information you provide. We
address above between 9 a.m. and 5 will also post a report summarizing each The FAA worked in conjunction with
p.m., Monday through Friday, except industry, under the Airworthiness
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
substantive verbal contact we receive
Federal holidays. about this proposed AD. Directive Implementation Aviation
For service information identified in Rulemaking Committee (ARC), to
this proposed AD, contact Boeing Discussion enhance the AD system. One
Commercial Airplanes, Attention: Data We have received reports of cracking enhancement was a new process for
& Services Management, P.O. Box 3707, at certain fastener locations in the annotating which steps in the service
MC 2H–65, Seattle, WA 98124–2207; window corners of the window belt. At information are required for compliance
telephone 206–544–5000, extension 1; the time of the crack detection, the with an AD. Differentiating these steps
fax 206–766–5680; Internet https:// airplanes had accumulated between from other tasks in the service
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![15524 Federal Register / Vol. 80, No. 56 / Tuesday, March 24, 2015 / Proposed Rules
information is expected to improve an accordance with the operator’s require repairing those conditions in
owner’s/operator’s understanding of maintenance or inspection program one of the following ways:
crucial AD requirements and help without obtaining approval of an • In accordance with a method that
provide consistent judgment in AD alternative method of compliance we approve; or
compliance. The steps identified as RC (AMOC), provided the steps identified
• Using data that meet the
(required for compliance) in any service as RC can be done and the airplane can
certification basis of the airplane, and
information identified previously have a be put back in a serviceable condition.
that have been approved by the Boeing
direct effect on detecting, preventing, Any substitutions or changes to steps
Commercial Airplanes Organization
resolving, or eliminating an identified identified as RC will require approval of
Designation Authorization (ODA) whom
unsafe condition. an AMOC.
we have authorized to make those
Steps that are identified as RC in any Differences Between This Proposed AD findings.
service information must be done to and the Service Information
Costs of Compliance
comply with the proposed AD. Boeing Alert Service Bulletin 737–
However, steps that are not identified as 53A1328, dated July 22, 2014, specifies We estimate that this proposed AD
RC are recommended. Those steps that to contact the manufacturer for affects 142 airplanes of U.S. registry.
are not identified as RC may be deviated instructions on how to repair certain We estimate the following costs to
from using accepted methods in conditions, but this proposed AD would comply with this proposed AD:
ESTIMATED COSTS: REQUIRED ACTIONS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspection .......................... Up to 2,312 work-hours × $85 per hour = $0 Up to $196,520 per in- Up to $27,905,840 per
$196,520 per inspection cycle. spection cycle. inspection cycle.
ESTIMATED COSTS: OPTIONAL ACTIONS
Action Labor cost Parts cost Cost per product
Preventive modification ..... 108 work-hours × $85 per hour = $9,180 ................................................. $0 $9,180.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be proposed inspection. We have no way of might need repairs:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Repair ............................... Up to 18 work-hours × $85 per hour = $1,530 per repair ......................... $0 Up to $1,530 per repair.
Authority for This Rulemaking Regulatory Findings under the criteria of the Regulatory
Flexibility Act.
Title 49 of the United States Code We determined that this proposed AD
specifies the FAA’s authority to issue would not have federalism implications List of Subjects in 14 CFR Part 39
rules on aviation safety. Subtitle I, under Executive Order 13132. This
Air transportation, Aircraft, Aviation
section 106, describes the authority of proposed AD would not have a
safety, Incorporation by reference,
the FAA Administrator. Subtitle VII: substantial direct effect on the States, on
Safety.
Aviation Programs, describes in more the relationship between the national
detail the scope of the Agency’s Government and the States, or on the The Proposed Amendment
authority. distribution of power and
responsibilities among the various Accordingly, under the authority
We are issuing this rulemaking under levels of government. delegated to me by the Administrator,
the authority described in Subtitle VII, the FAA proposes to amend 14 CFR part
For the reasons discussed above, I
Part A, Subpart III, Section 44701: 39 as follows:
certify this proposed regulation:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with (1) Is not a ‘‘significant regulatory PART 39—AIRWORTHINESS
promoting safe flight of civil aircraft in action’’ under Executive Order 12866, DIRECTIVES
air commerce by prescribing regulations (2) Is not a ‘‘significant rule’’ under
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
for practices, methods, and procedures the DOT Regulatory Policies and ■ 1. The authority citation for part 39
the Administrator finds necessary for Procedures (44 FR 11034, February 26, continues to read as follows:
safety in air commerce. This regulation 1979), Authority: 49 U.S.C. 106(g), 40113, 44701.
is within the scope of that authority (3) Will not affect intrastate aviation
because it addresses an unsafe condition in Alaska, and § 39.13 [Amended]
that is likely to exist or develop on (4) Will not have a significant ■ 2. The FAA amends § 39.13 by adding
products identified in this rulemaking economic impact, positive or negative, the following new airworthiness
action. on a substantial number of small entities directive (AD):
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![Federal Register / Vol. 80, No. 56 / Tuesday, March 24, 2015 / Proposed Rules 15525
The Boeing Company: Docket No. FAA– and corrective actions, must be done in 98057–3356; phone: 425–917–6447; fax: 425–
2015–0495; Directorate Identifier 2014– accordance with Part 3 of the 917–6590; email: haytham.alaidy@faa.gov.
NM–172–AD. Accomplishment Instructions of Boeing Alert (2) For service information identified in
Service Bulletin 737–53A1328, dated July 22, this AD, contact Boeing Commercial
(a) Comments Due Date Airplanes, Attention: Data & Services
2014, except as required by paragraph (i)(2)
We must receive comments by May 8, of this AD. Management, P.O. Box 3707, MC 2H–65,
2015. Seattle, WA 98124–2207; telephone 206–
(i) Exceptions to the Service Bulletin 544–5000, extension 1; fax 206–766–5680;
(b) Affected ADs Specifications Internet https://www.myboeingfleet.com. You
None. (1) Where Boeing Alert Service Bulletin may view the referenced service information
737–53A1328, dated July 22, 2014, specifies at the FAA, Transport Airplane Directorate,
(c) Applicability
a compliance time ‘‘after the original issue 1601 Lind Avenue SW., Renton, WA. For
This AD applies to The Boeing Company date of this service bulletin,’’ this AD information on the availability of this
Model 737–300, –400, and –500 series requires compliance within the specified material at the FAA, call 425–227–1221.
airplanes, certificated in any category, as compliance time after the effective date of
identified in Boeing Alert Service Bulletin Issued in Renton, Washington, on March
this AD. 13, 2015.
737–53A1328, dated July 22, 2014.
(2) Where Boeing Alert Service Bulletin Jeffrey E. Duven,
(d) Subject 737–53A1328, dated July 22, 2014, specifies
Manager, Transport Airplane Directorate,
Air Transport Association (ATA) of to contact Boeing for repair instructions:
Aircraft Certification Service.
America Code 53, Fuselage. Before further flight, repair the cracking
using a method approved in accordance with [FR Doc. 2015–06574 Filed 3–23–15; 8:45 am]
(e) Unsafe Condition the procedures specified in paragraph (j) of BILLING CODE 4910–13–P
This AD was prompted by reports of this AD.
fatigue cracking at certain fastener locations (j) Alternative Methods of Compliance
in the window corners of the window belt (AMOCs)
DEPARTMENT OF TRANSPORTATION
area. We are issuing this AD to detect and
correct fatigue cracking around the fastener (1) The Manager, Seattle Aircraft Federal Aviation Administration
locations that could cause multiple window Certification Office (ACO), FAA, has the
corner skin cracks, which could result in authority to approve AMOCs for this AD, if 14 CFR Part 39
rapid decompression and loss of structural requested using the procedures found in 14
integrity of the airplane. CFR 39.19. In accordance with 14 CFR 39.19, [Docket No. FAA–2015–0493; Directorate
send your request to your principal inspector Identifier 2014–NM–184–AD]
(f) Compliance or local Flight Standards District Office, as
RIN 2120–AA64
Comply with this AD within the appropriate. If sending information directly
compliance times specified, unless already to the manager of the ACO, send it to the
attention of the person identified in
Airworthiness Directives; Lockheed
done.
paragraph (k)(1) of this AD. Information may Martin Corporation/Lockheed Martin
(g) Inspections be emailed to: 9-ANM-Seattle-ACO-AMOC- Aeronautics Company Airplanes
At the applicable time specified in tables Requests@faa.gov. AGENCY: Federal Aviation
1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of (2) Before using any approved AMOC,
Administration (FAA), DOT.
Boeing Alert Service Bulletin 737–53A1328, notify your appropriate principal inspector,
dated July 22, 2014, except as required by or lacking a principal inspector, the manager ACTION: Notice of proposed rulemaking
paragraph (i)(1) of this AD: Do external of the local flight standards district office/ (NPRM).
surface high frequency eddy current (HFEC) certificate holding district office.
inspections for cracking of the skin at the 12 (3) If any service information contains SUMMARY: We propose to adopt a new
fastener locations at the upper forward and steps that are identified as RC (Required for airworthiness directive (AD) for certain
lower aft corners of each window between Compliance), those steps must be done to Lockheed Martin Corporation/Lockheed
station (STA) 360 and STA 540 and between comply with this AD; any steps that are not Martin Aeronautics Company Model
STA 727 and STA 908, left-side and right- identified as RC are recommended. Those 188 series airplanes. This proposed AD
side of the fuselage, at and between stringers steps that are not identified as RC may be was prompted by an evaluation by the
S–11 and S–13, and all applicable related deviated from using accepted methods in design approval holder (DAH)
investigative and corrective actions, in accordance with the operator’s maintenance indicating that the upper and lower
accordance with the Accomplishment or inspection program without obtaining
wing skin planks at the attachment of
Instructions of Boeing Alert Service Bulletin approval of an AMOC, provided the steps
737–53A1328, dated July 22, 2014, except as identified as RC can be done and the airplane
the main landing gear (MLG) ribs at
required by paragraph (i)(2) of this AD. Do all can be put back in a serviceable condition. certain wing-stations are subject to
applicable related investigative and Any substitutions or changes to steps widespread fatigue damage (WFD). This
corrective actions before further flight. identified as RC require approval of an proposed AD would require an
Repeat the inspections at the applicable AMOC. inspection (for cracking) and
times specified in tables 1 and 2 of paragraph (4) An AMOC that provides an acceptable modification of the chordwise fastener
1.E., ‘‘Compliance,’’ of Boeing Alert Service level of safety may be used for any repair rows of the upper and lower wing
Bulletin 737–53A1328, dated July 22, 2014, required by this AD if it is approved by the planks at the attachments to the MLG
until the terminating action specified in Boeing Commercial Airplanes Organization ribs at certain wing-stations. We are
paragraph (h) of this AD is done. Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
proposing this AD to prevent fatigue
(h) Optional Preventive Modification ACO, to make those findings. For a repair cracking of the upper and lower wing
Accomplishment of a preventive method to be approved, the repair must meet skin planks at the attachment of the
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
modification in the fastener locations in the the certification basis of the airplane, and the MLG ribs, which could result in failure
window corners of the window belt area approval must specifically refer to this AD. of the wing.
between station (STA) 360 and STA 540 and DATES: We must receive comments on
between STA 727 and STA 908, left-side and (k) Related Information
this proposed AD by May 8, 2015.
right-side fuselage, at and between stringers (1) For more information about this AD,
S–11 and S–13, terminates the inspections contact Haytham Alaidy, Aerospace ADDRESSES: You may send comments,
required by paragraph (g) of this AD at the Engineer, Airframe Branch, ANM–120S, using the procedures found in 14 CFR
modified location only. The modification, FAA, Seattle Aircraft Certification Office 11.43 and 11.45, by any of the following
including all applicable related investigative (ACO), 1601 Lind Avenue SW., Renton, WA methods:
VerDate Sep<11>2014 18:30 Mar 23, 2015 Jkt 235001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\24MRP1.SGM 24MRP1](https://thefederalregister.org/doc/80_FR_15579/page/3.svg)
Document Created: 2015-12-18 11:45:06
Document Modified: 2015-12-18 11:45:06
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by May 8, 2015. | |
| Contact | Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6573; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 15523 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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