81 FR 19512 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 65 (April 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 65 (April 5, 2016)
| Page Range | 19512-19514 | |
| FR Document | 2016-07577 |
[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)] [Proposed Rules] [Pages 19512-19514] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-07577] [[Page 19512]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5042; Directorate Identifier 2015-NM-140-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 all The Boeing Company Model 737-600, -700, -700C, -800, -900 and -900ER series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fastener locations in the window corner surround structure are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive high frequency eddy current (HFEC) inspections for cracking in certain fastener locations in the window corner surround structure, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking around certain fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and consequent reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by May 20, 2016. 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 NPRM, 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-2016- 5042. 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-2016- 5042; 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: Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6595; fax: 425-917-6590; email: [email protected]. 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-2016-5042; Directorate Identifier 2015-NM-140-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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty [[Page 19513]] regarding the LOV applicable to their airplanes. The FAA has received a report indicating that an evaluation by the DAH has indicated that certain fastener locations in the window corner surround structure are subject to WFD. Fatigue cracking around certain fastener locations could cause multiple window corner skin cracks, which could result in rapid decompression and consequent reduced structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015. The service information describes procedures for HFEC inspections for cracking in certain fastener locations in the window corner surround structure and repair. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. 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, except as discussed under ``Difference Between this Proposed AD and the Service Information.'' For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5042. Difference Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015, 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 1,528 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection...................... 38 work-hours x $0 [per inspection $3,230 [per $4,935,440 [per $85 per hour = cycle]. inspection cycle]. inspection $3,230 [per cycle]. inspection cycle]. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed 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 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): The Boeing Company: Docket No. FAA-2016-5042; Directorate Identifier 2015-NM-140-AD. (a) Comments Due Date We must receive comments by May 20, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 737-600, -700, - 700C, -800, -900 and -900ER series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fastener locations in the window corner surround structure are subject to [[Page 19514]] widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking around certain fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and consequent reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Repair At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015: Do an external high frequency eddy current (HFEC) inspection for cracking of the skin around the fastener locations at the upper forward and lower aft corners of each window between station (STA) 360 and STA 540, as applicable, and at the lower forward and upper aft corners of each window between STA 727 and STA 887, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015. Repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015. If any crack is found during any inspection, repair before further flight using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (h) Exception to the Service Bulletin Specifications Although Boeing Alert Service Bulletin 737-53A1351, dated July 8, 2015, specifies to contact Boeing for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (i) 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 (j)(1) of this AD. Information may be emailed to: [email protected]. (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, modification, or alteration 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. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) Except as required by paragraph (h) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information (1) For more information about this AD, contact Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6595; fax: 425-917-6590; email: [email protected]. (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 24, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-07577 Filed 4-4-16; 8:45 am] BILLING CODE 4910-13-P
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DEPARTMENT OF TRANSPORTATION the FAA, Transport Airplane incidents such as material defects, poor
Directorate, 1601 Lind Avenue SW., fabrication quality, or corrosion pits,
Federal Aviation Administration Renton, WA. For information on the dings, or scratches. Fatigue damage can
availability of this material at the FAA, occur locally, in small areas or
14 CFR Part 39 call 425–227–1221. It is also available structural design details, or globally.
[Docket No. FAA–2016–5042; Directorate on the Internet at http:// Global fatigue damage is general
Identifier 2015–NM–140–AD] www.regulations.gov by searching for degradation of large areas of structure
and locating Docket No. FAA–2016– with similar structural details and stress
RIN 2120–AA64 5042. levels. Multiple-site damage is global
Examining the AD Docket damage that occurs in a large structural
Airworthiness Directives; The Boeing
element such as a single rivet line of a
Company Airplanes You may examine the AD docket on lap splice joining two large skin panels.
AGENCY: Federal Aviation the Internet at http:// Global damage can also occur in
Administration (FAA), DOT. www.regulations.gov by searching for multiple elements such as adjacent
and locating Docket No. FAA–2016– frames or stringers. Multiple-site-
ACTION: Notice of proposed rulemaking
5042; or in person at the Docket damage and multiple-element-damage
(NPRM). Management Facility between 9 a.m. cracks are typically too small initially to
SUMMARY: We propose to adopt a new and 5 p.m., Monday through Friday, be reliably detected with normal
airworthiness directive (AD) for all The except Federal holidays. The AD docket inspection methods. Without
Boeing Company Model 737–600, –700, contains this proposed AD, the intervention, these cracks will grow,
–700C, –800, –900 and –900ER series regulatory evaluation, any comments and eventually compromise the
airplanes. This proposed AD was received, and other information. The structural integrity of the airplane, in a
prompted by an evaluation by the street address for the Docket Office condition known as WFD. As an
design approval holder (DAH) (phone: 800–647–5527) is in the airplane ages, WFD will likely occur,
indicating that certain fastener locations ADDRESSES section. Comments will be
and will certainly occur if the airplane
in the window corner surround available in the AD docket shortly after is operated long enough without any
structure are subject to widespread receipt. intervention.
fatigue damage (WFD). This proposed FOR FURTHER INFORMATION CONTACT:
The FAA’s WFD final rule (75 FR
AD would require repetitive high Jason Deutschman, Aerospace Engineer, 69746, November 15, 2010) became
frequency eddy current (HFEC) Airframe Branch, ANM–120S, FAA, effective on January 14, 2011. The WFD
inspections for cracking in certain Seattle Aircraft Certification Office rule requires certain actions to prevent
fastener locations in the window corner (ACO), 1601 Lind Avenue SW., Renton, structural failure due to WFD
surround structure, and repair if WA 98057–3356; phone: 425–917–6595; throughout the operational life of
necessary. We are proposing this AD to fax: 425–917–6590; email: certain existing transport category
detect and correct fatigue cracking jason.deutschman@faa.gov. airplanes and all of these airplanes that
around certain fastener locations that SUPPLEMENTARY INFORMATION: will be certificated in the future. For
could cause multiple window corner Comments Invited existing and future airplanes subject to
skin cracks, which could result in rapid the WFD rule, the rule requires that
decompression and consequent reduced We invite you to send any written
DAHs establish a limit of validity (LOV)
structural integrity of the airplane. relevant data, views, or arguments about
of the engineering data that support the
this proposal. Send your comments to
DATES: We must receive comments on
an address listed under the ADDRESSES structural maintenance program.
this proposed AD by May 20, 2016. section. Include ‘‘Docket No. FAA– Operators affected by the WFD rule may
ADDRESSES: You may send comments, 2016–5042; Directorate Identifier 2015– not fly an airplane beyond its LOV,
using the procedures found in 14 CFR NM–140–AD’’ at the beginning of your unless an extended LOV is approved.
11.43 and 11.45, by any of the following comments. We specifically invite The WFD rule (75 FR 69746,
methods: comments on the overall regulatory, November 15, 2010) does not require
• Federal eRulemaking Portal: Go to economic, environmental, and energy identifying and developing maintenance
http://www.regulations.gov. Follow the aspects of this proposed AD. We will actions if the DAHs can show that such
instructions for submitting comments. consider all comments received by the actions are not necessary to prevent
• Fax: 202–493–2251. closing date and may amend this WFD before the airplane reaches the
• Mail: U.S. Department of proposed AD because of those LOV. Many LOVs, however, do depend
Transportation, Docket Operations, M– comments. on accomplishment of future
30, West Building Ground Floor, Room We will post all comments we maintenance actions. As stated in the
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http:// WFD rule, any maintenance actions
Washington, DC 20590. www.regulations.gov, including any necessary to reach the LOV will be
• Hand Delivery: Deliver to Mail personal information you provide. We mandated by airworthiness directives
address above between 9 a.m. and 5 will also post a report summarizing each through separate rulemaking actions.
p.m., Monday through Friday, except substantive verbal contact we receive In the context of WFD, this action is
Federal holidays. about this proposed AD. necessary to enable DAHs to propose
For service information identified in LOVs that allow operators the longest
Discussion
Lhorne on DSK5TPTVN1PROD with PROPOSALS
this NPRM, contact Boeing Commercial operational lives for their airplanes, and
Airplanes, Attention: Data & Services Structural fatigue damage is still ensure that WFD will not occur.
Management, P.O. Box 3707, MC 2H–65, progressive. It begins as minute cracks, This approach allows for an
Seattle, WA 98124–2207; telephone: and those cracks grow under the action implementation strategy that provides
206–544–5000, extension 1; fax: 206– of repeated stresses. This can happen flexibility to DAHs in determining the
766–5680; Internet: https:// because of normal operational timing of service information
www.myboeingfleet.com. You may view conditions and design attributes, or development (with FAA approval),
this referenced service information at because of isolated situations or while providing operators with certainty
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![Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 19513
regarding the LOV applicable to their through their normal course of business Difference Between This Proposed AD
airplanes. or by the means identified in the and the Service Information
The FAA has received a report ADDRESSES section.
indicating that an evaluation by the Boeing Alert Service Bulletin 737–
DAH has indicated that certain fastener FAA’s Determination 53A1351, dated July 8, 2015, specifies to
locations in the window corner We are proposing this AD because we contact the manufacturer for
surround structure are subject to WFD. evaluated all the relevant information instructions on how to repair certain
Fatigue cracking around certain fastener and determined the unsafe condition conditions, but this proposed AD would
locations could cause multiple window described previously is likely to exist or require repairing those conditions in
corner skin cracks, which could result develop in other products of the same one of the following ways:
in rapid decompression and consequent type design. • In accordance with a method that
reduced structural integrity of the we approve; or
Proposed AD Requirements • Using data that meet the
airplane.
This proposed AD would require certification basis of the airplane, and
Related Service Information Under 1 accomplishing the actions specified in that have been approved by the Boeing
CFR Part 51 the service information identified Commercial Airplanes Organization
We reviewed Boeing Alert Service previously, except as discussed under Designation Authorization (ODA) whom
Bulletin 737–53A1351, dated July 8, ‘‘Difference Between this Proposed AD we have authorized to make those
2015. The service information describes and the Service Information.’’ For findings.
procedures for HFEC inspections for information on the procedures and Costs of Compliance
cracking in certain fastener locations in compliance times, see this service
the window corner surround structure information at http:// We estimate that this proposed AD
and repair. This service information is www.regulations.gov by searching for affects 1,528 airplanes of U.S. registry.
reasonably available because the and locating Docket No. FAA–2016– We estimate the following costs to
interested parties have access to it 5042. comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ...... 38 work-hours × $85 per hour $0 [per inspection cycle] ........ $3,230 [per inspection cycle] $4,935,440 [per inspection
= $3,230 [per inspection cycle].
cycle].
We have received no definitive data proposed AD would not have a PART 39—AIRWORTHINESS
that would enable us to provide cost substantial direct effect on the States, on DIRECTIVES
estimates for the on-condition actions the relationship between the national
specified in this proposed AD. Government and the States, or on the ■ 1. The authority citation for part 39
distribution of power and continues to read as follows:
Authority for This Rulemaking
responsibilities among the various Authority: 49 U.S.C. 106(g), 40113, 44701.
Title 49 of the United States Code levels of government.
specifies the FAA’s authority to issue § 39.13 [Amended]
For the reasons discussed above, I
rules on aviation safety. Subtitle I, certify this proposed regulation: ■ 2. The FAA amends § 39.13 by adding
section 106, describes the authority of the following new airworthiness
(1) Is not a ‘‘significant regulatory
the FAA Administrator. Subtitle VII: directive (AD):
action’’ under Executive Order 12866,
Aviation Programs, describes in more The Boeing Company: Docket No. FAA–
(2) Is not a ‘‘significant rule’’ under
detail the scope of the Agency’s 2016–5042; Directorate Identifier 2015–
the DOT Regulatory Policies and
authority. NM–140–AD.
Procedures (44 FR 11034, February 26,
We are issuing this rulemaking under (a) Comments Due Date
1979),
the authority described in Subtitle VII, We must receive comments by May 20,
Part A, Subpart III, Section 44701: (3) Will not affect intrastate aviation
in Alaska, and 2016.
‘‘General requirements.’’ Under that
section, Congress charges the FAA with (4) Will not have a significant (b) Affected ADs
promoting safe flight of civil aircraft in economic impact, positive or negative, None.
air commerce by prescribing regulations on a substantial number of small entities
(c) Applicability
for practices, methods, and procedures under the criteria of the Regulatory
Flexibility Act. This AD applies to all The Boeing
the Administrator finds necessary for Company Model 737–600, –700, –700C,
safety in air commerce. This regulation List of Subjects in 14 CFR Part 39 –800, –900 and –900ER series airplanes,
is within the scope of that authority certificated in any category.
because it addresses an unsafe condition Air transportation, Aircraft, Aviation
(d) Subject
Lhorne on DSK5TPTVN1PROD with PROPOSALS
that is likely to exist or develop on safety, Incorporation by reference,
products identified in this rulemaking Safety. Air Transport Association (ATA) of
action. America Code 53, Fuselage.
The Proposed Amendment
(e) Unsafe Condition
Regulatory Findings
Accordingly, under the authority This AD was prompted by an evaluation by
We determined that this proposed AD delegated to me by the Administrator, the design approval holder (DAH) indicating
would not have federalism implications the FAA proposes to amend 14 CFR part that certain fastener locations in the window
under Executive Order 13132. This 39 as follows: corner surround structure are subject to
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![19514 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules
widespread fatigue damage (WFD). We are deviation, or alteration deviation must meet AD was prompted by a report that static
issuing this AD to detect and correct fatigue the certification basis of the airplane and the strength analysis has shown that the
cracking around certain fastener locations approval must specifically refer to this AD. aluminum transmission aft bearing plate
that could cause multiple window corner (4) Except as required by paragraph (h) of
this AD: For service information that
assemblies have inadequate structural
skin cracks, which could result in rapid
decompression and consequent reduced contains steps that are labeled as RC, the strength for one or more of the required
structural integrity of the airplane. provisions of paragraphs (i)(4)(i) and (i)(4)(ii) load cases, including cases for drive
of this AD apply. system jam, flap skew, and structural
(f) Compliance (i) The steps labeled as RC, including damage tolerance. Inadequate structural
Comply with this AD within the substeps under an RC step and any figures strength can result in damage to the
compliance times specified, unless already identified in an RC step, must be done to transmission aft bearing plate
done. comply with the AD. An AMOC is required assemblies. This proposed AD would
for any deviations to RC steps, including
(g) Repetitive Inspections and Repair
substeps and identified figures.
require removing aluminum
At the applicable time specified in (ii) Steps not labeled as RC may be transmission aft bearing plate
paragraph 1.E., ‘‘Compliance,’’ of Boeing deviated from using accepted methods in assemblies from the flap track and
Alert Service Bulletin 737–53A1351, dated accordance with the operator’s maintenance installing titanium transmission aft
July 8, 2015: Do an external high frequency or inspection program without obtaining bearing plate assemblies to the flap
eddy current (HFEC) inspection for cracking approval of an AMOC, provided the RC steps, track. We are proposing this AD to
of the skin around the fastener locations at including substeps and identified figures, can prevent inadequate structural strength
the upper forward and lower aft corners of still be done as specified, and the airplane
each window between station (STA) 360 and
of transmission aft bearing plate
can be put back in an airworthy condition.
STA 540, as applicable, and at the lower assemblies. This condition could result
forward and upper aft corners of each (j) Related Information in damaged transmission aft bearing
window between STA 727 and STA 887, in (1) For more information about this AD, plate assemblies, which could result in
accordance with the Accomplishment contact Jason Deutschman, Aerospace incorrect operation and departure of the
Instructions of Boeing Alert Service Bulletin Engineer, Airframe Branch, ANM–120S, flap from the airplane and consequent
737–53A1351, dated July 8, 2015. Repeat the FAA, Seattle ACO, 1601 Lind Avenue SW., loss of controllability of the airplane.
inspection thereafter at the applicable times Renton, WA 98057–3356; phone: 425–917–
specified in paragraph 1.E., ‘‘Compliance,’’ of DATES: We must receive comments on
6595; fax: 425–917–6590; email:
Boeing Alert Service Bulletin 737–53A1351, jason.deutschman@faa.gov. this proposed AD by May 20, 2016.
dated July 8, 2015. If any crack is found (2) For service information identified in ADDRESSES: You may send comments,
during any inspection, repair before further this AD, contact Boeing Commercial using the procedures found in 14 CFR
flight using a method approved in Airplanes, Attention: Data & Services 11.43 and 11.45, by any of the following
accordance with the procedures specified in Management, P.O. Box 3707, MC 2H–65, methods:
paragraph (i) of this AD. Seattle, WA 98124–2207; telephone: 206–
• Federal eRulemaking Portal: Go to
544–5000, extension 1; fax: 206–766–5680;
(h) Exception to the Service Bulletin http://www.regulations.gov. Follow the
Internet: https://www.myboeingfleet.com.
Specifications instructions for submitting comments.
You may view the referenced service
Although Boeing Alert Service Bulletin information at the FAA, Transport Airplane • Fax: 202–493–2251.
737–53A1351, dated July 8, 2015, specifies to Directorate, 1601 Lind Avenue SW., Renton, • Mail: U.S. Department of
contact Boeing for repair instructions, and WA. For information on the availability of Transportation, Docket Operations, M–
specifies that action as ‘‘RC’’ (Required for this material at the FAA, call 425–227–1221. 30, West Building Ground Floor, Room
Compliance), this AD requires repair before
Issued in Renton, Washington, on March W12–140, 1200 New Jersey Avenue SE.,
further flight using a method approved in
accordance with the procedures specified in 24, 2016. Washington, DC 20590.
paragraph (i) of this AD. Michael Kaszycki, • Hand Delivery: Deliver to Mail
Acting Manager, Transport Airplane address above between 9 a.m. and 5
(i) Alternative Methods of Compliance p.m., Monday through Friday, except
(AMOCs) Directorate, Aircraft Certification Service.
[FR Doc. 2016–07577 Filed 4–4–16; 8:45 am] Federal holidays.
(1) The Manager, Seattle Aircraft For service information identified in
Certification Office (ACO), FAA, has the BILLING CODE 4910–13–P
this NPRM, contact Boeing Commercial
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
Airplanes, Attention: Data & Services
CFR 39.19. In accordance with 14 CFR 39.19, DEPARTMENT OF TRANSPORTATION Management, P.O. Box 3707, MC 2H–65,
send your request to your principal inspector Seattle, WA 98124–2207; telephone
or local Flight Standards District Office, as Federal Aviation Administration 206–544–5000, extension 1; fax 206–
appropriate. If sending information directly 766–5680; Internet https://
to the manager of the ACO, send it to the 14 CFR Part 39 www.myboeingfleet.com. You may view
attention of the person identified in this referenced service information at
paragraph (j)(1) of this AD. Information may [Docket No. FAA–2016–5041; Directorate
Identifier 2015–NM–102–AD] the FAA, Transport Airplane
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov.
Directorate, 1601 Lind Avenue SW.,
RIN 2120–AA64 Renton, WA. For information on the
(2) Before using any approved AMOC,
notify your appropriate principal inspector, availability of this material at the FAA,
Airworthiness Directives; The Boeing call 425–227–1221. It is also available
or lacking a principal inspector, the manager
of the local flight standards district office/ Company Airplanes on the Internet at http://
certificate holding district office. AGENCY: Federal Aviation www.regulations.gov by searching for
Lhorne on DSK5TPTVN1PROD with PROPOSALS
(3) An AMOC that provides an acceptable Administration (FAA), DOT. and locating Docket No. FAA–2016–
level of safety may be used for any repair, 5041.
modification, or alteration required by this ACTION: Notice of proposed rulemaking
AD if it is approved by the Boeing (NPRM). Examining the AD Docket
Commercial Airplanes Organization
Designation Authorization (ODA) that has SUMMARY: We propose to adopt a new You may examine the AD docket on
been authorized by the Manager, Seattle airworthiness directive (AD) for certain the Internet at http://
ACO, to make those findings. To be The Boeing Company Model 747–8 and www.regulations.gov by searching for
approved, the repair method, modification 747–8F series airplanes. This proposed and locating Docket No. FAA–2016–
VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\05APP1.SGM 05APP1](https://thefederalregister.org/doc/81_FR_19577/page/3.svg)
Document Created: 2018-02-07 13:53:50
Document Modified: 2018-02-07 13:53:50
| 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 20, 2016. | |
| Contact | Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6595; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 19512 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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