81 FR 9367 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 37 (February 25, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 37 (February 25, 2016)
| Page Range | 9367-9370 | |
| FR Document | 2016-03698 |
[Federal Register Volume 81, Number 37 (Thursday, February 25, 2016)] [Proposed Rules] [Pages 9367-9370] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-03698] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-3703; Directorate Identifier 2015-NM-115-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. [[Page 9368]] ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, and -400ER series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the skin lap splice is subject to widespread fatigue damage (WFD). This proposed AD would require repetitive external detailed and surface high frequency eddy current (HFEC) inspections of the outer skin for cracking around fastener heads common to the inboard fastener row of the skin lap splice. We are proposing this AD to detect and correct fatigue cracking of the skin lap splice, which, if not detected, could grow and result in possible rapid decompression and reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by April 11, 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-2016-3703. 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- 3703; 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: Wayne Lockett, 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: [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-2016-3703; Directorate Identifier 2015-NM-115-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 ADs 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 regarding the LOV applicable to their airplanes. We have received an evaluation by the DAH indicating that the skin lap splice is subject to WFD. As a result of WFD analysis, the stringer S-2R skin lap splice from station (STA) 368 to STA 434 requires additional supplemental inspection beyond the inspections specified in the Boeing Model 767 airplane maintenance planning document. This condition, if not corrected, could result in cracking of the skin lap splice, which could grow and result in possible rapid [[Page 9369]] decompression and reduced structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 767-53A0260, dated August 26, 2014. The service information describes procedures for a detailed inspection and a surface HFEC inspection at section 41, stringer S-2R skin lap splice from STA 368 to STA 434, for any cracking, 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 described previously, except as discussed under ``Differences 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-2016-3703.'' 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. Costs of Compliance We estimate that this proposed AD affects 356 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 ---------------------------------------------------------------------------------------------------------------- Inspections...................... 3 work-hours x $85 $0 $255 per inspection $90,780 per per hour = $255 per cycle. inspection 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-2016-3703; Directorate Identifier 2015-NM-115-AD. (a) Comments Due Date We must receive comments by April 11, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the Boeing Company Model 767-200, -300, and - 400ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767-53A0260, dated August 26, 2014. (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 indicating that the skin lap splice is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of this skin lap splice, which, if not detected, could grow and result in possible rapid decompression and reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Actions At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 767-53A0260, dated August 26, 2014, except as required by paragraph (h) of this AD: Do a detailed inspection and a surface high frequency eddy current (HFEC) inspection at section 41, stringer S-2R skin lap splice from body station (STA) 368 to STA 434, for any cracking, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert [[Page 9370]] Service Bulletin 767-53A0260, dated August 26, 2014. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 767-53A0260, dated August 26, 2014. If any existing external repair is found in the inspection area, then the inspections in Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0260, dated August 26, 2014, are not required in the area hidden by the repair, provided that the repair was previously approved by the Manager, Seattle Aircraft Certification Office (ACO), or by the Authorized Representative of the Boeing Commercial Airplanes Organization Designation Authorization (ODA), or installed as specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0260, dated August 26, 2014. Inspections in Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0260, dated August 26, 2014, remain applicable in areas not hidden by the repair. (h) Exception to the Service Information Where Boeing Alert Service Bulletin 767-53A0260, dated August 26, 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. (i) 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 paragraph (i) 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 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 Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) 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 Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; 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 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. Issued in Renton, Washington, on February 15, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-03698 Filed 2-24-16; 8:45 am] BILLING CODE 4910-13-P
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Issued in Renton, Washington, on February and 5 p.m., Monday through Friday, have the failure mode (failure of the
16, 2016. except Federal holidays. The AD docket hydraulic actuator rod end or attach
Dionne Palermo, contains this AD action, the NPRM (76 fitting due to severe wear-out) addressed
Acting Manager, Transport Airplane FR 15864, March 22, 2011), the in the NPRM. Based on field reports and
Directorate, Aircraft Certification Service. regulatory evaluation, any comments design review, the manufacturer found
[FR Doc. 2016–03996 Filed 2–24–16; 8:45 am] received, and other information. The that certain hydraulic actuators do not
BILLING CODE 4910–13–P address for the Docket Office (telephone have this failure mode. Based on this
800–647–5527) is the Docket new manufacturer finding, a new safety
Management Facility, U.S. Department analysis was conducted and we
DEPARTMENT OF TRANSPORTATION of Transportation, Docket Operations, determined that this issue is no longer
M–30, West Building Ground Floor, a safety concern.
Federal Aviation Administration Room W12–140, 1200 New Jersey
FAA’s Conclusions
Avenue SE., Washington, DC 20590.
14 CFR Part 39 Upon further consideration, we have
FOR FURTHER INFORMATION CONTACT: Tak
[Docket No. FAA–2011–0254; Directorate Kobayashi, Aerospace Engineer, determined that the safety concern
Identifier 2010–NM–180–AD] Propulsion Branch, ANM–140S, FAA, identified in the NPRM does not affect
Seattle Aircraft Certification Office, The Boeing Company Model 737–600,
RIN 2120–AA64 –700, –700C, –800, –900, and –900ER
1601 Lind Avenue SW., Renton, WA
Airworthiness Directives; The Boeing 98057–3356; phone: 425–917–6499; fax: series airplanes identified in the NPRM.
Company Airplanes 425–917–6590; email: Accordingly, the NPRM is withdrawn.
Takahisa.Kobayashi@faa.gov. Withdrawal of the NPRM does not
AGENCY: Federal Aviation preclude the FAA from issuing another
SUPPLEMENTARY INFORMATION:
Administration (FAA), Department of related action or commit the FAA to any
Transportation (DOT). Discussion course of action in the future.
ACTION: Proposed rule; withdrawal. We proposed to amend part 39 of the Regulatory Impact
Federal Aviation Regulations (14 CFR
SUMMARY: The FAA withdraws a notice Since this action only withdraws an
part 39) with a notice of proposed
of proposed rulemaking (NPRM) that NPRM, it is neither a proposed nor a
rulemaking (NPRM) for a new AD for
proposed a new airworthiness directive final rule and therefore is not covered
certain The Boeing Company Model
(AD), which would have applied to under Executive Order 12866, the
737–600, –700, –700C, –800, –900, and
certain The Boeing Company Model Regulatory Flexibility Act, or DOT
–900ER series airplanes. The NPRM
737–600, –700, –700C, –800, –900, and Regulatory Policies and Procedures (44
published in the Federal Register on
–900ER series airplanes. For certain FR 11034, February 26, 1979).
March 22, 2011 (76 FR 15864) (‘‘the
airplanes, the NPRM would have
NPRM’’). For certain airplanes, the List of Subjects in 14 CFR Part 39
required a one-time inspection for
NPRM would have required a one-time Air transportation, Aircraft, Aviation
damage of the hydraulic actuator rod
inspection for damage of the hydraulic safety, Incorporation by reference,
ends and actuator attach fittings on the
actuator rod ends and actuator attach Safety.
thrust reversers, and repair or
fittings on the thrust reversers, and
replacement if necessary. For all The Withdrawal
repair or replacement if necessary. For
airplanes, the NPRM would have
all airplanes, the NPRM would have Accordingly, we withdraw the NPRM,
required repetitive inspections for
required repetitive inspections for Docket No. FAA–2011–0254, Directorate
damage of the hydraulic actuator rod
damage of the hydraulic actuator rod Identifier 2010–NM–180–AD, which
ends, attach bolts, and nuts; repetitive
ends, attach bolts, and nuts; repetitive was published in the Federal Register
inspections for damage of fitting
inspections for damage of fitting on March 22, 2011 (76 FR 15864).
assemblies, wear spacers, and actuator
assemblies, wear spacers, and actuator
attach fittings on the thrust reverser; Issued in Renton, Washington, on February
attach fittings on the thrust reverser;
repetitive measurements of the wear 15, 2016.
repetitive measurements of the wear
spacer; and corrective actions if Michael Kaszycki,
spacer; and corrective actions if
necessary. Since the NPRM was issued, Acting Manager, Transport Airplane
necessary.
the manufacturer notified us that an Directorate, Aircraft Certification Service.
The NPRM was prompted by reports
assumption regarding a failure mode of [FR Doc. 2016–03693 Filed 2–24–16; 8:45 am]
of in-service damage of the attachment
the rod ends or attachment fittings for
fittings for the thrust reverser actuator. BILLING CODE 4910–13–P
the thrust reverser actuator used in the
The proposed actions were intended to
original safety assessment was incorrect.
detect and correct such damage, which
A new safety analysis was conducted DEPARTMENT OF TRANSPORTATION
could result in actuator attach fitting
and we determined that this issue is no
failure, loss of the thrust reverser auto Federal Aviation Administration
longer a safety concern. Accordingly,
restow function, and consequent loss of
the NPRM is withdrawn.
control of the airplane. 14 CFR Part 39
DATES: As of February 25, 2016, the
proposed rule, which was published in Actions Since NPRM Was Issued
[Docket No. FAA–2016–3703; Directorate
rmajette on DSK2TPTVN1PROD with PROPOSALS
the Federal Register on March 22, 2011 Since we issued the NPRM, the Identifier 2015–NM–115–AD]
(76 FR 15864), is withdrawn. manufacturer has notified us that an
assumption regarding a failure mode of RIN 2120–AA64
ADDRESSES: You may examine the AD
docket on the Internet at http:// the attachment fittings for the thrust Airworthiness Directives; The Boeing
www.regulations.gov by searching for reverser actuator used in the original Company Airplanes
and locating Docket No. FAA–2011– safety assessment was incorrect. It was
0254; or in person at the Docket originally assumed that all hydraulic AGENCY:Federal Aviation
Management Facility between 9 a.m. actuators attached to the thrust reverser Administration (FAA), DOT.
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decompression and reduced structural FAA’s Determination information at http://
integrity of the airplane. www.regulations.gov by searching for
We are proposing this AD because we
Related Service Information Under 1 and locating Docket No. FAA–2016–
evaluated all the relevant information
CFR Part 51 3703.’’
and determined the unsafe condition
We reviewed Boeing Alert Service described previously is likely to exist or The phrase ‘‘corrective actions’’ is
Bulletin 767–53A0260, dated August 26, develop in other products of the same used in this proposed AD. ‘‘Corrective
2014. The service information describes type design. actions’’ are actions that correct or
procedures for a detailed inspection and address any condition found. Corrective
Proposed AD Requirements
a surface HFEC inspection at section 41, actions in an AD could include, for
stringer S–2R skin lap splice from STA This proposed AD would require example, repairs.
368 to STA 434, for any cracking, and accomplishing the actions specified in
the service information described Costs of Compliance
repair. This service information is
reasonably available because the previously, except as discussed under We estimate that this proposed AD
interested parties have access to it ‘‘Differences Between this Proposed AD affects 356 airplanes of U.S. registry.
through their normal course of business and the Service Information.’’ For
or by the means identified in the information on the procedures and We estimate the following costs to
ADDRESSES section. compliance times, see this service comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections ......... 3 work-hours × $85 per hour = $0 $255 per inspection cycle .............. $90,780 per inspection cycle.
$255 per inspection cycle.
We have received no definitive data For the reasons discussed above, I (a) Comments Due Date
that would enable us to provide cost certify this proposed regulation: We must receive comments by April 11,
estimates for the on-condition actions (1) Is not a ‘‘significant regulatory 2016.
specified in this proposed AD. action’’ under Executive Order 12866, (b) Affected ADs
Authority for This Rulemaking (2) Is not a ‘‘significant rule’’ under None.
the DOT Regulatory Policies and
Title 49 of the United States Code Procedures (44 FR 11034, February 26, (c) Applicability
specifies the FAA’s authority to issue 1979), This AD applies to the Boeing Company
rules on aviation safety. Subtitle I, Model 767–200, –300, and –400ER series
(3) Will not affect intrastate aviation airplanes, certificated in any category, as
section 106, describes the authority of in Alaska, and identified in Boeing Alert Service Bulletin
the FAA Administrator. Subtitle VII: (4) Will not have a significant 767–53A0260, dated August 26, 2014.
Aviation Programs, describes in more economic impact, positive or negative,
detail the scope of the Agency’s (d) Subject
on a substantial number of small entities
authority. under the criteria of the Regulatory Air Transport Association (ATA) of
America Code 53, Fuselage.
We are issuing this rulemaking under Flexibility Act.
the authority described in Subtitle VII, (e) Unsafe Condition
Part A, Subpart III, Section 44701: List of Subjects in 14 CFR Part 39
This AD was prompted by an evaluation by
‘‘General requirements.’’ Under that Air transportation, Aircraft, Aviation the design approval holder indicating that
section, Congress charges the FAA with safety, Incorporation by reference, the skin lap splice is subject to widespread
promoting safe flight of civil aircraft in Safety. fatigue damage. We are issuing this AD to
air commerce by prescribing regulations detect and correct fatigue cracking of this
for practices, methods, and procedures The Proposed Amendment skin lap splice, which, if not detected, could
grow and result in possible rapid
the Administrator finds necessary for Accordingly, under the authority decompression and reduced structural
safety in air commerce. This regulation delegated to me by the Administrator, integrity of the airplane.
is within the scope of that authority the FAA proposes to amend 14 CFR part
because it addresses an unsafe condition 39 as follows: (f) Compliance
that is likely to exist or develop on Comply with this AD within the
products identified in this rulemaking PART 39—AIRWORTHINESS compliance times specified, unless already
action. DIRECTIVES done.
Regulatory Findings (g) Inspection and Corrective Actions
■ 1. The authority citation for part 39
At the applicable time specified in
We determined that this proposed AD continues to read as follows: paragraph 1.E., ‘‘Compliance,’’ of Boeing
would not have federalism implications Authority: 49 U.S.C. 106(g), 40113, 44701. Alert Service Bulletin 767–53A0260, dated
rmajette on DSK2TPTVN1PROD with PROPOSALS
under Executive Order 13132. This August 26, 2014, except as required by
§ 39.13 [Amended] paragraph (h) of this AD: Do a detailed
proposed AD would not have a
■ 2. The FAA amends § 39.13 by adding inspection and a surface high frequency eddy
substantial direct effect on the States, on
current (HFEC) inspection at section 41,
the relationship between the national the following new airworthiness
stringer S–2R skin lap splice from body
Government and the States, or on the directive (AD): station (STA) 368 to STA 434, for any
distribution of power and The Boeing Company: Docket No. FAA– cracking, and do all applicable corrective
responsibilities among the various 2016–3703; Directorate Identifier 2015– actions, in accordance with the
levels of government. NM–115–AD. Accomplishment Instructions of Boeing Alert
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Service Bulletin 767–53A0260, dated August (ii) Steps not labeled as RC may be add requirements to install new barrel
26, 2014. Do all applicable corrective actions deviated from using accepted methods in nuts at the forward engine mounts; or
before further flight. Repeat the inspections accordance with the operator’s maintenance identify the part number of the barrel
thereafter at the applicable times specified in or inspection program without obtaining nuts, inspect affected barrel nuts for
paragraph 1.E., ‘‘Compliance,’’ of Boeing approval of an AMOC, provided the RC steps,
Alert Service Bulletin 767–53A0260, dated including substeps and identified figures, can
gaps of the strut bulkhead and forward
August 26, 2014. If any existing external still be done as specified, and the airplane engine mount, and do related
repair is found in the inspection area, then can be put back in an airworthy condition. investigative and corrective actions if
the inspections in Part 1 of the necessary. This proposed AD would
Accomplishment Instructions of Boeing Alert (j) Related Information also remove airplanes from the
Service Bulletin 767–53A0260, dated August (1) For more information about this AD, applicability. We are proposing this AD
26, 2014, are not required in the area hidden contact Wayne Lockett, Aerospace Engineer, to detect and correct cracked barrel nuts
by the repair, provided that the repair was Airframe Branch, ANM–120S, FAA, Seattle on a forward engine mount, which
previously approved by the Manager, Seattle ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6447; fax: 425–
could result in reduced load capacity of
Aircraft Certification Office (ACO), or by the
Authorized Representative of the Boeing 917–6590; email: wayne.lockett@faa.gov. the forward engine mount, separation of
Commercial Airplanes Organization (2) For service information identified in an engine under power from the
Designation Authorization (ODA), or this AD, contact Boeing Commercial airplane, and consequent loss of control
installed as specified in Part 2 of the Airplanes, Attention: Data & Services of the airplane.
Accomplishment Instructions of Boeing Alert Management, P.O. Box 3707, MC 2H–65, DATES: We must receive comments on
Service Bulletin 767–53A0260, dated August Seattle, WA 98124–2207; telephone: 206– this proposed AD by April 11, 2016.
26, 2014. Inspections in Part 1 of the 544–5000, extension 1; fax: 206–766–5680;
Accomplishment Instructions of Boeing Alert Internet https://www.myboeingfleet.com. You ADDRESSES: You may send comments,
Service Bulletin 767–53A0260, dated August may view this referenced service information using the procedures found in 14 CFR
26, 2014, remain applicable in areas not at the FAA, Transport Airplane Directorate, 11.43 and 11.45, by any of the following
hidden by the repair. 1601 Lind Avenue SW., Renton, WA. For methods:
information on the availability of this • Federal eRulemaking Portal: Go to
(h) Exception to the Service Information material at the FAA, call 425–227–1221. http://www.regulations.gov. Follow the
Where Boeing Alert Service Bulletin 767– instructions for submitting comments.
Issued in Renton, Washington, on February
53A0260, dated August 26, 2014, specifies a
15, 2016. • Fax: 202–493–2251.
compliance time ‘‘after the original issue date
of this service bulletin,’’ this AD requires Michael Kaszycki, • Mail: U.S. Department of
compliance within the specified compliance Acting Manager, Transport Airplane Transportation, Docket Operations, M–
time after the effective date of this AD. Directorate, Aircraft Certification Service. 30, West Building Ground Floor, Room
[FR Doc. 2016–03698 Filed 2–24–16; 8:45 am] W12–140, 1200 New Jersey Avenue SE.,
(i) Alternative Methods of Compliance
BILLING CODE 4910–13–P Washington, DC 20590.
(AMOCs)
• Hand Delivery: Deliver to Mail
(1) The Manager, Seattle ACO, FAA, has address above between 9 a.m. and 5
the authority to approve AMOCs for this AD,
DEPARTMENT OF TRANSPORTATION p.m., Monday through Friday, except
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19, Federal holidays.
send your request to your principal inspector Federal Aviation Administration For service information identified in
or local Flight Standards District Office, as this NPRM, contact Boeing Commercial
appropriate. If sending information directly 14 CFR Part 39 Airplanes, Attention: Data & Services
to the manager of the ACO, send it to the [Docket No. FAA–2016–3702; Directorate Management, P. O. Box 3707, MC 2H–
attention of the person identified in Identifier 2015–NM–103–AD] 65, Seattle, WA 98124–2207; telephone:
paragraph (i) of this AD. Information may be 206–544–5000, extension 1; fax: 206–
emailed to: 9-ANM-Seattle-ACO-AMOC- RIN 2120–AA64 766–5680; Internet https://
Requests@faa.gov.
www.myboeingfleet.com. You may view
(2) Before using any approved AMOC, Airworthiness Directives; The Boeing
notify your appropriate principal inspector, this referenced service information at
Company Airplanes
or lacking a principal inspector, the manager the FAA, Transport Airplane
of the local flight standards district office/ AGENCY: Federal Aviation Directorate, 1601 Lind Avenue SW.,
certificate holding district office. Administration (FAA), DOT. Renton, WA. For information on the
(3) An AMOC that provides an acceptable ACTION: Notice of proposed rulemaking availability of this material at the FAA,
level of safety may be used for any repair, (NPRM). call 425–227–1221. It is also available
modification, or alteration required by this on the Internet at http://
AD if it is approved by the Boeing SUMMARY: We propose to supersede www.regulations.gov by searching for
Commercial Airplanes ODA that has been Airworthiness Directive (AD) 2013–24– and locating Docket No. FAA–2016–
authorized by the Manager, Seattle ACO, to 12, which applies to all The Boeing
make those findings. To be approved, the 3702.
repair method, modification deviation, or
Company Model 747–8 and 747–8F
airplanes. AD 2013–24–12 currently Examining the AD Docket
alteration deviation must meet the
certification basis of the airplane, and the requires repetitive ultrasonic or dye You may examine the AD docket on
approval must specifically refer to this AD. penetrant inspections for cracking of the the Internet at http://
(4) Except as required by paragraph (h) of barrel nuts and bolts on each forward www.regulations.gov by searching for
this AD: For service information that engine mount, and related investigative and locating Docket No. FAA–2016–
rmajette on DSK2TPTVN1PROD with PROPOSALS
contains steps that are labeled as Required and corrective actions if necessary. 3702; or in person at the Docket
for Compliance (RC), the provisions of Since we issued AD 2013–24–12, we Management Facility between 9 a.m.
paragraphs (i)(4)(i) and (i)(4)(ii) apply. have determined that it is necessary to and 5 p.m., Monday through Friday,
(i) The steps labeled as RC, including
substeps under an RC step and any figures
mandate the installation of new barrel except Federal holidays. The AD docket
identified in an RC step, must be done to nuts or new inspections to adequately contains this proposed AD, the
comply with the AD. An AMOC is required address the unsafe condition. This regulatory evaluation, any comments
for any deviations to RC steps, including proposed AD would retain the received, and other information. The
substeps and identified figures. requirements of AD 2013–24–12 and street address for the Docket Office
VerDate Sep<11>2014 13:27 Feb 24, 2016 Jkt 238001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\25FEP1.SGM 25FEP1](https://thefederalregister.org/doc/81_FR_9404/page/4.svg)
Document Created: 2018-02-02 14:35:39
Document Modified: 2018-02-02 14:35:39
| 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 April 11, 2016. | |
| Contact | Wayne Lockett, 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: [email protected] | |
| FR Citation | 81 FR 9367 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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