80 FR 38408 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 128 (July 6, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 128 (July 6, 2015)
| Page Range | 38408-38410 | |
| FR Document | 2015-16296 |
[Federal Register Volume 80, Number 128 (Monday, July 6, 2015)] [Proposed Rules] [Pages 38408-38410] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-16296] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2456; Directorate Identifier 2015-NM-032-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 767 airplanes. This proposed AD was prompted by reports of cracking at a central part of the structure. This proposed AD would require repetitive inspections of the skin hidden by the upper and lower splice fittings on both sides of the fuselage, and corrective action if necessary. We are proposing this AD to detect and correct fatigue cracking of the hidden fuselage skin and cracking, corrosion, and other damage to the splice fittings and adjacent visible fuselage skin and structure that could lead to loss of a primary load path between the fuselage and the wing box, and consequent reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by August 20, 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- 2456. 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- 2456; 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: wayne.lockett@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-2015-2456; Directorate Identifier 2015-NM-032-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 While replacing a cracked underwing longeron fitting, a crack indication was found in the STA 786 ring chord at the tension bolt hole common to the wing front spar lower chord and the internal bathtub fittings. There were two similar reports of these findings from two separate operators. The airplanes in these reports had 14,367 and 18,354 flight cycles and 90,389 and 96,826 flight hours, respectively. The current inspections in the Model 767 Maintenance Planning Document are not sufficient to detect any possible fuselage skin crack in the area adjacent to the ring chord at STA 786 before the crack extends to a critical length. The fuselage skin in this area is hidden between the splice fittings on the external side of the fuselage and the bathtub fittings on the internal side. This condition, if not corrected, could result in loss of a primary load path between the fuselage and the wing box, and consequent reduced structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 767-53A0263, dated January [[Page 38409]] 12, 2015. The service information describes procedures for repetitive inspections of the skin and splice fittings at stringer 29, body station 786 ring chord. 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 of this NPRM. 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.'' Refer to this service information for details on the procedures and compliance times. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 767-53A0263, dated January 12, 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 430 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...................... 9 work-hours x $85 per $0 $765 per inspection $328,950 per hour = $765 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. Explanation of ``RC (Required for Compliance)'' 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 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. For service information that contains steps that are labeled as Required for Compliance (RC), the following provisions apply: (1) 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, and an AMOC is required for any deviations to RC steps, including substeps and identified figures; and (2) 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. 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-2015-2456; Directorate Identifier 2015-NM-032-AD. [[Page 38410]] (a) Comments Due Date We must receive comments by August 20, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 767-200, -300, - 300F, and -400ER 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 reports of cracking at the station (STA 786) ring chord at the tension bolt hole common to the wing front spar lower chord and the internal bathtub fittings. We are issuing this AD to detect and correct fatigue cracking of the hidden fuselage skin and cracking, corrosion, and other damage to the splice fittings and adjacent visible fuselage skin and structure that could lead to loss of a primary load path between the fuselage and the wing box, and consequent reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 767-53A0263, dated January 12, 2015, except as required by paragraph (h) of this AD, do external ultrasonic and detailed inspections to detect cracking, corrosion, or other damage at the splice fitting location, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0263, dated January 12, 2015. (1) If cracking, corrosion, or other damage is not found, repeat the inspections at intervals not to exceed 6,000 flight cycles or 18,000 flight hours, whichever occurs first. Accomplishing a repair as specified in paragraph (g)(2) of this AD terminates the repetitive inspections in the repaired area only. (2) If any cracking, corrosion, or other damage is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. The repetitive inspections of paragraph (g)(1) are terminated in the repaired area only. (h) Exceptions to Service Information Specifications Where Boeing Alert Service Bulletin 767-53A0263, dated January 12, 2015, 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 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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by 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. (4) 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 Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6447; fax: 425-917-6590; email: wayne.lockett@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 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 June 24, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-16296 Filed 7-2-15; 8:45 am] BILLING CODE 4910-13-P
![38408 Federal Register / Vol. 80, No. 128 / Monday, July 6, 2015 / Proposed Rules
to which the AMOC applies, notify your reports of cracking at a central part of ADDRESSES section. Comments will be
appropriate principal inspector (PI) in the the structure. This proposed AD would available in the AD docket shortly after
FAA Flight Standards District Office (FSDO), require repetitive inspections of the skin receipt.
or lacking a PI, your local FSDO. hidden by the upper and lower splice FOR FURTHER INFORMATION CONTACT:
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
fittings on both sides of the fuselage, Wayne Lockett, Aerospace Engineer,
a manufacturer or other source, use these and corrective action if necessary. We Airframe Branch, ANM–120S, FAA,
actions if they are FAA-approved. Corrective are proposing this AD to detect and Seattle Aircraft Certification Office
actions are considered FAA-approved if they correct fatigue cracking of the hidden (ACO), 1601 Lind Avenue SW., Renton,
are approved by the State of Design Authority fuselage skin and cracking, corrosion, WA 98057–3356; phone: 425–917–6447;
(or their delegated agent). You are required and other damage to the splice fittings fax: 425–917–6590; email:
to assure the product is airworthy before it and adjacent visible fuselage skin and wayne.lockett@faa.gov.
is returned to service. structure that could lead to loss of a SUPPLEMENTARY INFORMATION:
(h) Related Information primary load path between the fuselage
and the wing box, and consequent Comments Invited
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2015–0071, dated reduced structural integrity of the We invite you to send any written
April 30, 2015; Piaggio Aero Industries S.p.A. airplane. relevant data, views, or arguments about
Service Bulletin 80–0081, Original Issue, DATES: We must receive comments on this proposal. Send your comments to
dated: April 28, 1997; Piaggio Aero Industries
this proposed AD by August 20, 2015. an address listed under the ADDRESSES
S.p.A. Service Bulletin 80–0081, Revision section. Include ‘‘Docket No. FAA–
No. 1, dated: May 11, 2010; or Piaggio Aero ADDRESSES: You may send comments,
2015–2456; Directorate Identifier 2015–
Industries S.p.A. Service Bulletin 80–0081, using the procedures found in 14 CFR NM–032–AD’’ at the beginning of your
Revision No. 2, dated: July 19, 2010, for 11.43 and 11.45, by any of the following comments. We specifically invite
related information. You may examine the methods: comments on the overall regulatory,
MCAI on the Internet at http:// • Federal eRulemaking Portal: Go to economic, environmental, and energy
www.regulations.gov by searching for and http://www.regulations.gov. Follow the
locating Docket No. FAA–2015–2466. For aspects of this proposed AD. We will
instructions for submitting comments. consider all comments received by the
service information related to this AD,
• Fax: 202–493–2251. closing date and may amend this
contact Piaggio Aero Industries S.p.A,
Airworthiness Office, Viale Generale • Mail: U.S. Department of proposed AD because of those
Disegna, 1–17038 Villanova d’Albenga, Transportation, Docket Operations, M– comments.
Savona, Italy; telephone: +39 010 6481800; 30, West Building Ground Floor, Room We will post all comments we
fax: +39 010 6481374; email: W12–140, 1200 New Jersey Avenue SE., receive, without change, to http://
technicalsupport@piaggioaerospace.it; Washington, DC 20590. www.regulations.gov, including any
Internet: www.piaggioaerospace.it/en/ • Hand Delivery: Deliver to Mail personal information you provide. We
customer-support#care. You may review this address above between 9 a.m. and 5
referenced service information at the FAA,
will also post a report summarizing each
p.m., Monday through Friday, except substantive verbal contact we receive
Small Airplane Directorate, 901 Locust, Federal holidays.
Kansas City, Missouri 64106. For information about this proposed AD.
For service information identified in
on the availability of this material at the Discussion
FAA, call (816) 329–4148. this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data While replacing a cracked underwing
Issued in Kansas City, Missouri, on June & Services Management, P.O. Box 3707,
25, 2015.
longeron fitting, a crack indication was
MC 2H–65, Seattle, WA 98124–2207; found in the STA 786 ring chord at the
Earl Lawrence, telephone 206–544–5000, extension 1; tension bolt hole common to the wing
Manager, Small Airplane Directorate, Aircraft fax 206 766 5680; Internet https:// front spar lower chord and the internal
Certification Service. www.myboeingfleet.com. You may view bathtub fittings. There were two similar
[FR Doc. 2015–16293 Filed 7–2–15; 8:45 am] this referenced service information at reports of these findings from two
BILLING CODE 4910–13–P the FAA, Transport Airplane separate operators. The airplanes in
Directorate, 1601 Lind Avenue SW., these reports had 14,367 and 18,354
Renton, WA. For information on the flight cycles and 90,389 and 96,826
DEPARTMENT OF TRANSPORTATION availability of this material at the FAA, flight hours, respectively. The current
call 425–227–1221. It is also available inspections in the Model 767
Federal Aviation Administration
on the Internet at http:// Maintenance Planning Document are
www.regulations.gov by searching for not sufficient to detect any possible
14 CFR Part 39
and locating Docket No. FAA–2015– fuselage skin crack in the area adjacent
[Docket No. FAA–2015–2456; Directorate 2456. to the ring chord at STA 786 before the
Identifier 2015–NM–032–AD] crack extends to a critical length. The
Examining the AD Docket
fuselage skin in this area is hidden
RIN 2120–AA64 You may examine the AD docket on between the splice fittings on the
the Internet at http:// external side of the fuselage and the
Airworthiness Directives; The Boeing
www.regulations.gov by searching for bathtub fittings on the internal side.
Company Airplanes
and locating Docket No. FAA–2015– This condition, if not corrected, could
AGENCY: Federal Aviation 2456; or in person at the Docket result in loss of a primary load path
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Administration (FAA), DOT. Management Facility between 9 a.m. between the fuselage and the wing box,
ACTION: Notice of proposed rulemaking and 5 p.m., Monday through Friday, and consequent reduced structural
(NPRM). except Federal holidays. The AD docket integrity of the airplane.
contains this proposed AD, the
SUMMARY: We propose to adopt a new regulatory evaluation, any comments Related Service Information Under 1
airworthiness directive (AD) for all The received, and other information. The CFR Part 51
Boeing Company Model 767 airplanes. street address for the Docket Office We reviewed Boeing Alert Service
This proposed AD was prompted by (phone: 800–647–5527) is in the Bulletin 767–53A0263, dated January
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![Federal Register / Vol. 80, No. 128 / Monday, July 6, 2015 / Proposed Rules 38409
12, 2015. The service information Proposed AD Requirements require repairing those conditions in
describes procedures for repetitive one of the following ways:
inspections of the skin and splice This proposed AD would require
accomplishing the actions specified in • In accordance with a method that
fittings at stringer 29, body station 786 we approve; or
ring chord. This service information is the service information described
reasonably available because the previously, except as discussed under • Using data that meet the
interested parties have access to it ‘‘Differences Between this Proposed AD certification basis of the airplane, and
through their normal course of business and the Service Information.’’ Refer to that have been approved by the Boeing
or by the means identified in the this service information for details on Commercial Airplanes Organization
ADDRESSES section of this NPRM. the procedures and compliance times. Designation Authorization (ODA) whom
we have authorized to make those
FAA’s Determination Differences Between This Proposed AD findings.
and the Service Information
We are proposing this AD because we Costs of Compliance
evaluated all the relevant information Boeing Alert Service Bulletin 767–
and determined the unsafe condition 53A0263, dated January 12, 2015, We estimate that this proposed AD
described previously is likely to exist or specifies to contact the manufacturer for affects 430 airplanes of U.S. registry. We
develop in other products of the same instructions on how to repair certain estimate the following costs to comply
type design. conditions, but this proposed AD would with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ................. 9 work-hours × $85 per hour = $765 per $0 $765 per inspection cycle ....... $328,950 per inspection cycle.
inspection cycle.
We have received no definitive data without obtaining approval of an responsibilities among the various
that would enable us to provide cost AMOC, provided the RC steps, levels of government.
estimates for the on-condition actions including substeps and identified For the reasons discussed above, I
specified in this proposed AD. figures, can still be done as specified, certify this proposed regulation:
and the airplane can be put back in an (1) Is not a ‘‘significant regulatory
Explanation of ‘‘RC (Required for action’’ under Executive Order 12866,
airworthy condition.
Compliance)’’ Steps in Service (2) Is not a ‘‘significant rule’’ under
Information Authority for This Rulemaking the DOT Regulatory Policies and
The FAA worked in conjunction with Procedures (44 FR 11034, February 26,
Title 49 of the United States Code
industry, under the Airworthiness 1979),
specifies the FAA’s authority to issue (3) Will not affect intrastate aviation
Directive Implementation Aviation rules on aviation safety. Subtitle I,
Rulemaking Committee (ARC), to in Alaska, and
section 106, describes the authority of (4) Will not have a significant
enhance the AD system. One the FAA Administrator. Subtitle VII:
enhancement was a new process for economic impact, positive or negative,
Aviation Programs, describes in more on a substantial number of small entities
annotating which steps in the service detail the scope of the Agency’s
information are required for compliance under the criteria of the Regulatory
authority. Flexibility Act.
with an AD. Differentiating these steps
from other tasks in the service We are issuing this rulemaking under
List of Subjects in 14 CFR Part 39
information is expected to improve an the authority described in Subtitle VII,
Part A, Subpart III, Section 44701: Air transportation, Aircraft, Aviation
owner’s/operator’s understanding of
‘‘General requirements.’’ Under that safety, Incorporation by reference,
crucial AD requirements and help
section, Congress charges the FAA with Safety.
provide consistent judgment in AD
compliance. The steps identified as RC promoting safe flight of civil aircraft in The Proposed Amendment
(required for compliance) in any service air commerce by prescribing regulations
for practices, methods, and procedures Accordingly, under the authority
information identified previously have a delegated to me by the Administrator,
direct effect on detecting, preventing, the Administrator finds necessary for
safety in air commerce. This regulation the FAA proposes to amend 14 CFR part
resolving, or eliminating an identified 39 as follows:
unsafe condition. is within the scope of that authority
For service information that contains because it addresses an unsafe condition PART 39—AIRWORTHINESS
steps that are labeled as Required for that is likely to exist or develop on DIRECTIVES
Compliance (RC), the following products identified in this rulemaking
provisions apply: (1) The steps labeled action. ■ 1. The authority citation for part 39
as RC, including substeps under an RC Regulatory Findings continues to read as follows:
step and any figures identified in an RC Authority: 49 U.S.C. 106(g), 40113, 44701.
Lhorne on DSK7TPTVN1PROD with PROPOSALS
step, must be done to comply with the We determined that this proposed AD
AD, and an AMOC is required for any would not have federalism implications § 39.13 [Amended]
deviations to RC steps, including under Executive Order 13132. This ■ 2. The FAA amends § 39.13 by adding
substeps and identified figures; and (2) proposed AD would not have a the following new airworthiness
steps not labeled as RC may be deviated substantial direct effect on the States, on directive (AD):
from using accepted methods in the relationship between the national The Boeing Company: Docket No. FAA–
accordance with the operator’s Government and the States, or on the 2015–2456; Directorate Identifier 2015–
maintenance or inspection program distribution of power and NM–032–AD.
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(a) Comments Due Date (i) Alternative Methods of Compliance Issued in Renton, Washington, on June 24,
We must receive comments by August 20, (AMOCs) 2015.
2015. (1) The Manager, Seattle Aircraft Dionne Palermo,
Certification Office (ACO), FAA, has the Acting Manager, Transport Airplane
(b) Affected ADs Directorate, Aircraft Certification Service.
authority to approve AMOCs for this AD, if
None. requested using the procedures found in 14 [FR Doc. 2015–16296 Filed 7–2–15; 8:45 am]
(c) Applicability CFR 39.19. In accordance with 14 CFR 39.19, BILLING CODE 4910–13–P
send your request to your principal inspector
This AD applies to all The Boeing
or local Flight Standards District Office, as
Company Model 767–200, –300, –300F, and
appropriate. If sending information directly FEDERAL TRADE COMMISSION
–400ER series airplanes, certificated in any
to the manager of the ACO, send it to the
category. 16 CFR Part 313
attention of the person identified in
(d) Subject paragraph (j)(1) of this AD. Information may RIN 3084–AB42
Air Transport Association (ATA) of be emailed to: 9-ANM-Seattle-ACO-AMOC-
America Code 53, Fuselage. Requests@faa.gov. Amendment to the Privacy of
(2) Before using any approved AMOC, Consumer Financial Information Rule
(e) Unsafe Condition notify your appropriate principal inspector, Under the Gramm-Leach-Bliley Act
This AD was prompted by reports of or lacking a principal inspector, the manager
cracking at the station (STA 786) ring chord of the local flight standards district office/ Correction
at the tension bolt hole common to the wing certificate holding district office. In proposed rule document 2015–
front spar lower chord and the internal (3) An AMOC that provides an acceptable 14328 beginning on page 36267 in the
bathtub fittings. We are issuing this AD to level of safety may be used for any repair
detect and correct fatigue cracking of the
issue of Wednesday, June 24, 2015,
required by this AD if it is approved by the make the following correction:
hidden fuselage skin and cracking, corrosion, Boeing Commercial Airplanes Organization
and other damage to the splice fittings and On page 36268, in the first column, in
Designation Authorization (ODA) that has the second full paragraph, in the second
adjacent visible fuselage skin and structure been authorized by the Manager, Seattle
that could lead to loss of a primary load path line, ‘‘August 17, 2015’’ should read
ACO, to make those findings. For a repair ‘‘August 31, 2015’’.
between the fuselage and the wing box, and
method to be approved, the repair must meet
consequent reduced structural integrity of the [FR Doc. C1 2015–14328 Filed 7–2–15; 8:45 am]
the certification basis of the airplane, and the
airplane. BILLING CODE 1505–01–D
approval must specifically refer to this AD.
(f) Compliance (4) For service information that contains
Comply with this AD within the steps that are labeled as Required for
Compliance (RC), the provisions of DEPARTMENT OF HOUSING AND
compliance times specified, unless already URBAN DEVELOPMENT
done. paragraphs (i)(4)(i) and (i)(4)(ii) apply.
(i) The steps labeled as RC, including
(g) Inspection 24 CFR Part 203
substeps under an RC step and any figures
At the applicable time specified in identified in an RC step, must be done to [Docket No. FR–5742–P–01]
paragraph 1.E., ‘‘Compliance,’’ of Boeing comply with the AD. An AMOC is required
RIN 2502–AJ23
Alert Service Bulletin 767–53A0263, dated for any deviations to RC steps, including
January 12, 2015, except as required by substeps and identified figures. Federal Housing Administration (FHA):
paragraph (h) of this AD, do external (ii) Steps not labeled as RC may be
ultrasonic and detailed inspections to detect
Single Family Mortgage Insurance
deviated from using accepted methods in Maximum Time Period for Filing
cracking, corrosion, or other damage at the accordance with the operator’s maintenance
splice fitting location, in accordance with the Insurance Claims, Curtailment of
or inspection program without obtaining Interest and Disallowance of Operating
Accomplishment Instructions of Boeing Alert approval of an AMOC, provided the RC steps,
Service Bulletin 767–53A0263, dated January Expenses Incurred Beyond Certain
including substeps and identified figures, can
12, 2015. Established Timeframes
still be done as specified, and the airplane
(1) If cracking, corrosion, or other damage
is not found, repeat the inspections at
can be put back in an airworthy condition. AGENCY: Office of the Assistant
intervals not to exceed 6,000 flight cycles or (j) Related Information
Secretary for Housing—Federal Housing
18,000 flight hours, whichever occurs first. Commissioner, HUD.
(1) For more information about this AD,
Accomplishing a repair as specified in ACTION: Proposed rule.
contact Wayne Lockett, Aerospace Engineer,
paragraph (g)(2) of this AD terminates the
Airframe Branch, ANM–120S, FAA, Seattle SUMMARY: This proposed rule would
repetitive inspections in the repaired area
Aircraft Certification Office (ACO), 1601 Lind establish the maximum time period
only.
(2) If any cracking, corrosion, or other Avenue SW., Renton, WA 98057–3356; within which an FHA-approved
damage is found, before further flight, repair phone: 425–917–6447; fax: 425–917–6590; mortgagee must file a claim with FHA
using a method approved in accordance with email: wayne.lockett@faa.gov. for insurance benefits. HUD’s current
the procedures specified in paragraph (i) of (2) For service information identified in regulations are silent with respect to a
this AD. The repetitive inspections of this AD, contact Boeing Commercial deadline by which a claim for insurance
paragraph (g)(1) are terminated in the Airplanes, Attention: Data & Services
benefits must be filed with FHA. Due to
repaired area only. Management, P.O. Box 3707, MC 2H–65,
the downturn in the housing market,
Seattle, WA 98124–2207; telephone 206–
Lhorne on DSK7TPTVN1PROD with PROPOSALS
(h) Exceptions to Service Information which resulted in a significant increase
544–5000, extension 1; fax 206–766–5680;
Specifications in mortgage defaults, some mortgagees
Internet https://www.myboeingfleet.com. You
Where Boeing Alert Service Bulletin 767– have refrained from promptly filing
may view this referenced service information
53A0263, dated January 12, 2015, specifies a claims for insurance benefits and
at the FAA, Transport Airplane Directorate,
compliance time ‘‘after the original issue date 1601 Lind Avenue SW., Renton, WA. For
instead have opted to wait and file
of this Service Bulletin,’’ this AD requires information on the availability of this
multiple claims with FHA at a single
compliance within the specified compliance material at the FAA, call 425–227–1221.
point in time. The uncertainty regarding
time after the effective date of this AD. a deadline by which a claim must be
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Document Created: 2015-12-15 13:17:53
Document Modified: 2015-12-15 13:17:53
| 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 August 20, 2015. | |
| 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 | 80 FR 38408 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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