82 FR 34885 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 143 (July 27, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 143 (July 27, 2017)
| Page Range | 34885-34888 | |
| FR Document | 2017-15558 |
[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)] [Proposed Rules] [Pages 34885-34888] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-15558] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0710; Directorate Identifier 2017-NM-019-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. This proposed AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. This proposed AD would require an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 11, 2017. 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- [[Page 34886]] 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 Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.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. 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-2017- 0710; 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 Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. 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-2017-0710; Directorate Identifier 2017-NM-019-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 based on 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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread 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. This condition is known as widespread fatigue damage (WFD). It is associated with general degradation of large areas of structure with similar structural details and stress levels. 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 regarding the LOV applicable to their airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017-0023, dated February 10, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4- 605R airplanes. The MCAI states: In response to the FAA Part 26 rule change concerning Widespread Fatigue Damage (WFD), all wing structural items of the A300-600 design deemed potentially susceptible to WFD were assessed. The top stringer joints at Rib 18 were highlighted as an area of uniform stress distribution, indicating that cracks may develop in adjacent stringers at the same time which is known as Multi Element Damage (MED). Each affected stringer joint consists of three main load transferring parts: An overlapping flange, two straps attached through the stringer web and a strap on the top flange. All the components of the joint are attached with fasteners. The fastener holes were the subject of a MED WFD analysis, which showed that cracking could occur from a number of the holes in the joint on stringers 11, 12, 13, 14, 15, 16, 17, and 18. This condition, if not detected and corrected, could reduce the structural integrity of the wing. Prompted by the conclusion of the WFD analysis, Airbus issued Service Bulletin (SB) A300-57-6118 to provide modification instructions. The modification will both re-life via oversizing and inspect via non-destructive test a defined number of stringer joint fastener holes at Rib 18. This modification will delay the onset of cracking at the stringer joint, providing it is completed at the specified time and will delay the requirement for subsequent inspection. For the reasons described above, this [EASA] AD requires a detailed visual inspection (DVI) [for damage, including cracking] of the upper wing skin and the top stringer joints at Rib 18, [and corrective action if necessary] and modification of the stringer joint couplings at Rib 18, on both wings [as applicable]. The modification includes a related investigative action, i.e., a special detailed (roto-probe) inspection for damage, including cracking, of the fastener holes in the upper wing skin, and corrective action if necessary. Corrective actions include repairing any damage. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0710. [[Page 34887]] Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-57-6118, Revision 01, dated January 31, 2017. This service information describes procedures for an inspection of the upper wing skin and top stringer joints at rib 18, and modification of the stringer joint couplings. 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 and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 65 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspections and modification.......... 37 work-hours x $85 per $4,770 $7,915 $514,475 hour = $3,145. ---------------------------------------------------------------------------------------------------------------- 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): Airbus: Docket No. FAA-2017-0710; Directorate Identifier 2017-NM- 019-AD. (a) Comments Due Date We must receive comments by September 11, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B4-605R, B4-622R, B4-603, C4-605R Variant F, B4-620, B4-622, and F4-605R airplanes, certificated in any category, all serial numbers except Model A300 F4-605R airplanes that have embodied Airbus modification 12699 in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. We are issuing this AD to detect and correct damage (including cracking) at the stringer joints, which could reduce the structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions For the purposes of this AD, the definitions in paragraphs (g)(1) through (g)(5) of this AD apply. (1) Group 1 airplanes are defined as Airbus Model A300 B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes. (2) Group 2 airplanes are defined as Airbus Model A300 C4-605 Variant F and F4-605R (if in pre-modification 12699 configuration) airplanes. (3) Short range (SR) is defined as airplanes with an average flight time of less than 1.5 flight hours per flight cycle. (4) Long range (LR) is defined as airplanes with an average flight time equal to or higher than 1.5 flight hours per flight cycle. (5) For determining the ``short range'' and ``long range'' airplanes, the average flight time is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD. (h) Inspection and Modification Not before exceeding the applicable lower thresholds as specified in table 1 to paragraph (h) of this AD, and within the compliance times specified in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, as applicable: Accomplish a detailed visual [[Page 34888]] inspection for damage (including cracking) of the upper wing skin and top stringer joints at rib 18 on both wings, do all applicable corrective actions, and do the applicable modification, including related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6118, Revision 01, dated January 31, 2017, except as required by paragraph (i) of this AD. Do all applicable modifications, related investigative actions, and corrective actions before further flight. (1) For Group 1, LR airplanes: Inspect at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD, whichever occurs later. (i) Before exceeding 32,500 flight cycles or 70,300 flight hours, whichever occurs first since first flight of the airplane. (ii) Within 700 flight cycles, 1,500 flight hours, or 12 months, whichever occurs first after the effective date of this AD. (2) For Group 1, SR airplanes: Inspect at the time specified in paragraphs (h)(2)(i) or (h)(2)(ii) of this AD, whichever occurs later. (i) Before exceeding 35,100 flight cycles or 52,600 flight hours, whichever occurs first since the first flight of the airplane. (ii) Within 700 flight cycles or 1,000 flight hours, or 12 months, whichever occurs first after the effective date of this AD. (3) For Group 2, LR airplanes: Inspect before exceeding 35,000 flight cycles or 75,700 flight hours, whichever occurs first since the first flight of the airplane. (4) For Group 2, SR airplanes: Inspect before exceeding 37,800 flight cycles or 56,700 flight hours, whichever occurs first since the first flight of the airplane. Table 1 to Paragraph (h) of This AD--Compliance Time Lower Thresholds ------------------------------------------------------------------------ Compliance time flight cycles (FC) or flight hours (FH), whichever Applicable airplanes occurs first since first flight of the airplane ------------------------------------------------------------------------ Group 1, LR....................... Not before exceeding 30,900 FC or 66,700 FH. Group 1, SR....................... Not before exceeding 28,700 FC or 43,000 FH. Group 2, LR....................... Not before exceeding 28,600 FC or 61,700 FH. Group 2, SR....................... Not before exceeding 34,400 FC or 51,600 FH. ------------------------------------------------------------------------ (i) Service Information Exception Where Airbus Service Bulletin A300-57-6118, Revision 01, dated January 31, 2017, specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (k)(2) of this AD. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-57-6118, dated June 30, 2015. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, 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 International Branch, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: [email protected]. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017-0023, dated February 10, 2017, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0710. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; fax 425-227-1149. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this 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 July 18, 2017. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-15558 Filed 7-26-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules 34885
parties and other sources; to protect the source system under 5 U.S.C. 552a(j)(2), respect to such access. Providing notice
privacy of third parties; and to safeguard DHS will claim the same exemptions for to individuals with respect to existence
classified information. Disclosure of those records that are claimed for the of records pertaining to them in the
information to the subject of the inquiry original primary systems of records from system of records or otherwise setting
could also permit the subject to avoid which they originated and claims any up procedures pursuant to which
detection or apprehension. additional exemptions set forth here. individuals may access and view
In appropriate circumstances, when Exemptions from these particular records pertaining to themselves in the
compliance would not appear to subsections are justified, on a case-by- system would undermine investigative
interfere with or adversely affect the law case basis to be determined at the time efforts and reveal the identities of
enforcement purposes of this system a request is made, for the following witnesses, and potential witnesses, and
and the overall law enforcement reasons: confidential informants.
process, the applicable exemptions may (a) From subsection (c)(3) (Accounting Dated: July 20, 2017.
be waived on a case by case basis. for Disclosures) because release of the
Jonathan R. Cantor,
A notice of system of records for DHS/ accounting of disclosures could alert the
subject of an investigation of an actual Acting Chief Privacy Officer, Department of
ALL–039 Foreign Access Management Homeland Security.
System of Records is also published in or potential criminal, civil, or regulatory
[FR Doc. 2017–15751 Filed 7–26–17; 8:45 am]
this issue of the Federal Register. violation to the existence of that
investigation and reveal investigative BILLING CODE 9110–9B–P
List of Subjects in 6 CFR Part 5 interest on the part of DHS as well as
Freedom of information, Privacy. the recipient agency. Disclosure of the
For the reasons stated in the accounting would therefore present a DEPARTMENT OF TRANSPORTATION
preamble, DHS proposes to amend serious impediment to law enforcement
efforts and efforts to preserve national Federal Aviation Administration
chapter I of title 6, Code of Federal
Regulations, as follows: security. Disclosure of the accounting
would also permit the individual who is 14 CFR Part 39
PART 5—DISCLOSURE OF RECORDS the subject of a record to impede the [Docket No. FAA–2017–0710; Directorate
AND INFORMATION investigation, to tamper with witnesses Identifier 2017–NM–019–AD]
or evidence, and to avoid detection or RIN 2120–AA64
■ 1. Revise the authority citation for part apprehension, which would undermine
5 to read as follows: the entire investigative process. When Airworthiness Directives; Airbus
Authority: 6 U.S.C. 101 et seq.; Pub. L. an investigation has been completed, Airplanes
107–296, 116 Stat. 2135; 5 U.S.C. 301. information on disclosures made may
■ 2. Amend appendix C to part 5 by continue to be exempted if the fact that AGENCY: Federal Aviation
adding paragraph 78 to read as follows: an investigation occurred remains Administration (FAA), DOT.
sensitive after completion. ACTION: Notice of proposed rulemaking
Appendix C to Part 5—DHS Systems of (NPRM).
(b) From subsection (d) (Access and
Records Exempt From the Privacy Act Amendment to Records) because access
* * * * * to the records contained in this system SUMMARY: We propose to adopt a new
78. The DHS/ALL–039 Foreign Access of records could inform the subject of an airworthiness directive (AD) for certain
Management System of Records consists investigation of an actual or potential Airbus Model A300 B4–600R series
of electronic and paper records and will criminal, civil, or regulatory violation to airplanes; Model A300 B4–603, B4–620,
be used by DHS and its components. the existence of that investigation and and B4–622 airplanes; Model A300 C4–
The DHS/ALL–039 Foreign Access reveal investigative interest on the part 605R Variant F airplanes; and Model
Management System of Records is a of DHS or another agency. Access to the A300 F4–605R airplanes. This proposed
repository of information held by DHS records could permit the individual AD was prompted by a determination
in connection with its several and who is the subject of a record to impede that the top stringer joints at rib 18 are
varied missions and functions, the investigation, to tamper with an area of uniform stress distribution,
including, but not limited to the witnesses or evidence, and to avoid which indicates that cracks may
enforcement of civil and criminal laws; detection or apprehension. Amendment develop in adjacent stringers at the same
investigations, inquiries, and of the records could interfere with time. This proposed AD would require
proceedings there under; and national ongoing investigations and law an inspection of the upper wing skin
security and intelligence activities. The enforcement activities and would and top stringer joints, and modification
DHS/ALL–039 Foreign Access impose an unreasonable administrative of the stringer joint couplings if
Management System of Records burden by requiring investigations to be necessary. We are proposing this AD to
contains information that is collected continually reinvestigated. In addition, address the unsafe condition on these
by, on behalf of, in support of, or in permitting access and amendment to products.
cooperation with DHS and its such information could disclose DATES: We must receive comments on
components and may contain personally security-sensitive information that this proposed AD by September 11,
identifiable information collected by could be detrimental to homeland 2017.
other federal, state, local, tribal, foreign, security. ADDRESSES: You may send comments,
or international government agencies. (f) From subsections (e)(4)(G), using the procedures found in 14 CFR
mstockstill on DSK30JT082PROD with PROPOSALS
The Secretary of Homeland Security, (e)(4)(H), and (e)(4)(I) (Agency 11.43 and 11.45, by any of the following
pursuant to 5 U.S.C. 552a(k)(1), (k)(2), Requirements) and (f) (Agency Rules), methods:
and (k)(5), has exempted this system because portions of this system are • Federal eRulemaking Portal: Go to
from the following provisions of the exempt from the individual access http://www.regulations.gov. Follow the
Privacy Act: 5 U.S.C. 552a(c)(3); (d); provisions of subsection (d) for the instructions for submitting comments.
(e)(1), (e)(4)(G), (e)(4)(H), (e)(4)(I); and reasons noted above, and therefore DHS • Fax: 202–493–2251.
(f). When a record received from another is not required to establish • Mail: U.S. Department of
system has been exempted in that requirements, rules, or procedures with Transportation, Docket Operations, M–
VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\27JYP1.SGM 27JYP1](https://thefederalregister.org/doc/82_FR_35028/page/1.svg)
![34886 Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules
30, West Building Ground Floor, Room substantive verbal contact we receive development (with FAA approval),
W12–140, 1200 New Jersey Avenue SE., about this proposed AD. while providing operators with certainty
Washington, DC 20590. regarding the LOV applicable to their
Discussion
• Hand Delivery: Deliver to Mail airplanes.
address above between 9 a.m. and 5 Fatigue damage can occur locally, in The European Aviation Safety Agency
p.m., Monday through Friday, except small areas or structural design details, (EASA), which is the Technical Agent
Federal holidays. or globally, in widespread areas. for the Member States of the European
For service information identified in Multiple-site damage is widespread Union, has issued EASA Airworthiness
this NPRM, contact Airbus SAS, damage that occurs in a large structural Directive 2017–0023, dated February 10,
Airworthiness Office—EAW, 1 Rond element such as a single rivet line of a 2017 (referred to after this as the
Point Maurice Bellonte, 31707 Blagnac lap splice joining two large skin panels. Mandatory Continuing Airworthiness
Cedex, France; telephone +33 5 61 93 36 Widespread damage can also occur in Information, or ‘‘the MCAI’’), to correct
96; fax +33 5 61 93 44 51; email multiple elements such as adjacent an unsafe condition for certain Airbus
account.airworth-eas@airbus.com; frames or stringers. Multiple-site Model A300 B4–600R series airplanes;
Internet http://www.airbus.com. You damage and multiple-element damage Model A300 B4–603, B4–620, and B4–
may view this referenced service cracks are typically too small initially to 622 airplanes; Model A300 C4–605R
information at the FAA, Transport be reliably detected with normal Variant F airplanes; and Model A300
Airplane Directorate, 1601 Lind Avenue inspection methods. Without F4–605R airplanes. The MCAI states:
SW., Renton, WA. For information on intervention, these cracks will grow,
In response to the FAA Part 26 rule change
the availability of this material at the and eventually compromise the
concerning Widespread Fatigue Damage
FAA, call 425–227–1221. structural integrity of the airplane. This (WFD), all wing structural items of the A300–
condition is known as widespread 600 design deemed potentially susceptible to
Examining the AD Docket fatigue damage (WFD). It is associated WFD were assessed. The top stringer joints
You may examine the AD docket on with general degradation of large areas at Rib 18 were highlighted as an area of
the Internet at http:// of structure with similar structural uniform stress distribution, indicating that
details and stress levels. As an airplane cracks may develop in adjacent stringers at
www.regulations.gov by searching for the same time which is known as Multi
and locating Docket No. FAA–2017– ages, WFD will likely occur, and will
certainly occur if the airplane is Element Damage (MED). Each affected
0710; or in person at the Docket stringer joint consists of three main load
Management Facility between 9 a.m. operated long enough without any transferring parts: An overlapping flange, two
and 5 p.m., Monday through Friday, intervention. straps attached through the stringer web and
except Federal holidays. The AD docket The FAA’s WFD final rule (75 FR a strap on the top flange. All the components
69746, November 15, 2010) became of the joint are attached with fasteners. The
contains this proposed AD, the
effective on January 14, 2011. The WFD fastener holes were the subject of a MED
regulatory evaluation, any comments
rule requires certain actions to prevent WFD analysis, which showed that cracking
received, and other information. The could occur from a number of the holes in
structural failure due to WFD
street address for the Docket Operations the joint on stringers 11, 12, 13, 14, 15, 16,
throughout the operational life of
office (telephone 800–647–5527) is in 17, and 18.
certain existing transport category
the ADDRESSES section. Comments will This condition, if not detected and
airplanes and all of these airplanes that
be available in the AD docket shortly corrected, could reduce the structural
will be certificated in the future. For integrity of the wing.
after receipt.
existing and future airplanes subject to Prompted by the conclusion of the WFD
FOR FURTHER INFORMATION CONTACT: Dan the WFD rule, the rule requires that analysis, Airbus issued Service Bulletin (SB)
Rodina, Aerospace Engineer, DAHs establish a limit of validity (LOV) A300–57–6118 to provide modification
International Branch, ANM–116, of the engineering data that support the instructions. The modification will both re-
Transport Airplane Directorate, FAA, structural maintenance program. life via oversizing and inspect via non-
1601 Lind Avenue SW., Renton, WA Operators affected by the WFD rule may destructive test a defined number of stringer
98057–3356; telephone 425–227–2125; not fly an airplane beyond its LOV, joint fastener holes at Rib 18. This
fax 425–227–1149. unless an extended LOV is approved. modification will delay the onset of cracking
at the stringer joint, providing it is completed
SUPPLEMENTARY INFORMATION: The WFD rule (75 FR 69746,
at the specified time and will delay the
November 15, 2010) does not require requirement for subsequent inspection.
Comments Invited
identifying and developing maintenance For the reasons described above, this
We invite you to send any written actions if the DAHs can show that such [EASA] AD requires a detailed visual
relevant data, views, or arguments about actions are not necessary to prevent inspection (DVI) [for damage, including
this proposal. Send your comments to WFD before the airplane reaches the cracking] of the upper wing skin and the top
an address listed under the ADDRESSES LOV. Many LOVs, however, do depend stringer joints at Rib 18, [and corrective
section. Include ‘‘Docket No. FAA– on accomplishment of future action if necessary] and modification of the
2017–0710; Directorate Identifier 2017– maintenance actions. As stated in the stringer joint couplings at Rib 18, on both
NM–019–AD’’ at the beginning of your wings [as applicable].
WFD rule, any maintenance actions
comments. We specifically invite necessary to reach the LOV will be The modification includes a related
comments on the overall regulatory, mandated by airworthiness directives investigative action, i.e., a special
economic, environmental, and energy through separate rulemaking actions. detailed (roto-probe) inspection for
aspects of this proposed AD. We will In the context of WFD, this action is damage, including cracking, of the
mstockstill on DSK30JT082PROD with PROPOSALS
consider all comments received by the necessary to enable DAHs to propose fastener holes in the upper wing skin,
closing date and may amend this LOVs that allow operators the longest and corrective action if necessary.
proposed AD based on those comments. operational lives for their airplanes, and Corrective actions include repairing any
We will post all comments we still ensure that WFD will not occur. damage. You may examine the MCAI in
receive, without change, to http:// This approach allows for an the AD docket on the Internet at http://
www.regulations.gov, including any implementation strategy that provides www.regulations.gov by searching for
personal information you provide. We flexibility to DAHs in determining the and locating Docket No. FAA–2017–
will also post a report summarizing each timing of service information 0710.
VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\27JYP1.SGM 27JYP1](https://thefederalregister.org/doc/82_FR_35028/page/2.svg)
![Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules 34887
Related Service Information Under 1 through their normal course of business MCAI and service information
CFR Part 51 or by the means identified in the referenced above. We are proposing this
ADDRESSES section. AD because we evaluated all pertinent
Airbus has issued Service Bulletin information and determined an unsafe
A300–57–6118, Revision 01, dated FAA’s Determination and Requirements
condition exists and is likely to exist or
January 31, 2017. This service of This Proposed AD
develop on other products of the same
information describes procedures for an This product has been approved by type design.
inspection of the upper wing skin and the aviation authority of another
top stringer joints at rib 18, and country, and is approved for operation Costs of Compliance
modification of the stringer joint in the United States. Pursuant to our We estimate that this proposed AD
couplings. This service information is bilateral agreement with the State of affects 65 airplanes of U.S. registry.
reasonably available because the Design Authority, we have been notified We estimate the following costs to
interested parties have access to it of the unsafe condition described in the comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspections and modification .......................... 37 work-hours × $85 per hour = $3,145 ........ $4,770 $7,915 $514,475
We have received no definitive data 2. Is not a ‘‘significant rule’’ under the airplanes that have embodied Airbus
that would enable us to provide cost DOT Regulatory Policies and Procedures modification 12699 in production.
estimates for the on-condition actions (44 FR 11034, February 26, 1979); (d) Subject
specified in this proposed AD. 3. Will not affect intrastate aviation in Air Transport Association (ATA) of
Alaska; and America Code 57, Wings.
Authority for This Rulemaking 4. Will not have a significant
economic impact, positive or negative, (e) Reason
Title 49 of the United States Code
on a substantial number of small entities This AD was prompted by a determination
specifies the FAA’s authority to issue that the top stringer joints at rib 18 are an
rules on aviation safety. Subtitle I, under the criteria of the Regulatory
Flexibility Act. area of uniform stress distribution, which
section 106, describes the authority of indicates that cracks may develop in adjacent
the FAA Administrator. ‘‘Subtitle VII: List of Subjects in 14 CFR Part 39 stringers at the same time. We are issuing this
Aviation Programs,’’ describes in more AD to detect and correct damage (including
Air transportation, Aircraft, Aviation cracking) at the stringer joints, which could
detail the scope of the Agency’s safety, Incorporation by reference,
authority. reduce the structural integrity of the wing.
Safety.
We are issuing this rulemaking under (f) Compliance
The Proposed Amendment Comply with this AD within the
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701: Accordingly, under the authority compliance times specified, unless already
General requirements.’’ Under that delegated to me by the Administrator, done.
section, Congress charges the FAA with the FAA proposes to amend 14 CFR part (g) Definitions
promoting safe flight of civil aircraft in 39 as follows: For the purposes of this AD, the definitions
air commerce by prescribing regulations in paragraphs (g)(1) through (g)(5) of this AD
for practices, methods, and procedures PART 39—AIRWORTHINESS apply.
the Administrator finds necessary for DIRECTIVES (1) Group 1 airplanes are defined as Airbus
safety in air commerce. This regulation Model A300 B4–603, B4–605R, B4–620, B4–
■ 1. The authority citation for part 39 622, and B4–622R airplanes.
is within the scope of that authority continues to read as follows: (2) Group 2 airplanes are defined as Airbus
because it addresses an unsafe condition Model A300 C4–605 Variant F and F4–605R
that is likely to exist or develop on Authority: 49 U.S.C. 106(g), 40113, 44701.
(if in pre-modification 12699 configuration)
products identified in this rulemaking § 39.13 [Amended] airplanes.
action. ■ 2. The FAA amends § 39.13 by adding (3) Short range (SR) is defined as airplanes
with an average flight time of less than 1.5
Regulatory Findings the following new airworthiness flight hours per flight cycle.
directive (AD): (4) Long range (LR) is defined as airplanes
We determined that this proposed AD Airbus: Docket No. FAA–2017–0710; with an average flight time equal to or higher
would not have federalism implications Directorate Identifier 2017–NM–019–AD. than 1.5 flight hours per flight cycle.
under Executive Order 13132. This (5) For determining the ‘‘short range’’ and
proposed AD would not have a (a) Comments Due Date ‘‘long range’’ airplanes, the average flight
substantial direct effect on the States, on We must receive comments by September time is the total accumulated flight hours,
the relationship between the national 11, 2017. counted from take-off to touch-down, divided
Government and the States, or on the by the total accumulated flight cycles at the
mstockstill on DSK30JT082PROD with PROPOSALS
(b) Affected ADs effective date of this AD.
distribution of power and None.
responsibilities among the various (h) Inspection and Modification
levels of government. (c) Applicability Not before exceeding the applicable lower
For the reasons discussed above, I This AD applies to Airbus Model A300 B4– thresholds as specified in table 1 to
certify this proposed regulation: 605R, B4–622R, B4–603, C4–605R Variant F, paragraph (h) of this AD, and within the
B4–620, B4–622, and F4–605R airplanes, compliance times specified in paragraphs
1. Is not a ‘‘significant regulatory certificated in any category, all serial (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, as
action’’ under Executive Order 12866; numbers except Model A300 F4–605R applicable: Accomplish a detailed visual
VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\27JYP1.SGM 27JYP1](https://thefederalregister.org/doc/82_FR_35028/page/3.svg)
![34888 Federal Register / Vol. 82, No. 143 / Thursday, July 27, 2017 / Proposed Rules
inspection for damage (including cracking) of (1) Alternative Methods of Compliance Issued in Renton, Washington, on July 18,
the upper wing skin and top stringer joints (AMOCs): The Manager, International 2017.
at rib 18 on both wings, do all applicable Branch, ANM–116, FAA, has the authority to Victor Wicklund,
corrective actions, and do the applicable approve AMOCs for this AD, if requested Acting Manager, Transport Airplane
modification, including related investigative using the procedures found in 14 CFR 39.19. Directorate, Aircraft Certification Service.
and corrective actions, in accordance with In accordance with 14 CFR 39.19, send your
[FR Doc. 2017–15558 Filed 7–26–17; 8:45 am]
the Accomplishment Instructions of Airbus request to your principal inspector or local
Service Bulletin A300–57–6118, Revision 01, BILLING CODE 4910–13–P
Flight Standards District Office, as
dated January 31, 2017, except as required by appropriate. If sending information directly
paragraph (i) of this AD. Do all applicable to the manager of the International Branch,
modifications, related investigative actions, send it to the attention of the person DEPARTMENT OF TRANSPORTATION
and corrective actions before further flight. identified in paragraph (l)(2) of this AD.
(1) For Group 1, LR airplanes: Inspect at Information may be emailed to: 9-ANM-116- Federal Aviation Administration
the time specified in paragraph (h)(1)(i) or AMOC-REQUESTS@faa.gov. Before using
(h)(1)(ii) of this AD, whichever occurs later. any approved AMOC, notify your appropriate 14 CFR Part 39
(i) Before exceeding 32,500 flight cycles or principal inspector, or lacking a principal
70,300 flight hours, whichever occurs first [Docket No. FAA–2017–0711; Directorate
inspector, the manager of the local flight Identifier 2017–NM–003–AD]
since first flight of the airplane. standards district office/certificate holding
(ii) Within 700 flight cycles, 1,500 flight district office. RIN 2120–AA64
hours, or 12 months, whichever occurs first (2) Contacting the Manufacturer: For any
after the effective date of this AD. Airworthiness Directives; The Boeing
requirement in this AD to obtain corrective
(2) For Group 1, SR airplanes: Inspect at Company Airplanes
actions from a manufacturer, the action must
the time specified in paragraphs (h)(2)(i) or
be accomplished using a method approved
(h)(2)(ii) of this AD, whichever occurs later.
by the Manager, International Branch, ANM–
AGENCY: Federal Aviation
(i) Before exceeding 35,100 flight cycles or Administration (FAA), DOT.
116, Transport Airplane Directorate, FAA; or
52,600 flight hours, whichever occurs first
the European Aviation Safety Agency ACTION: Notice of proposed rulemaking
since the first flight of the airplane.
(ii) Within 700 flight cycles or 1,000 flight (EASA); or Airbus’s EASA Design (NPRM).
hours, or 12 months, whichever occurs first Organization Approval (DOA). If approved by
the DOA, the approval must include the SUMMARY: We propose to adopt a new
after the effective date of this AD.
(3) For Group 2, LR airplanes: Inspect DOA-authorized signature. airworthiness directive (AD) for certain
before exceeding 35,000 flight cycles or (3) Required for Compliance (RC): If any The Boeing Company Model 757–200,
75,700 flight hours, whichever occurs first service information contains procedures or –200CB, and –300 series airplanes. This
since the first flight of the airplane. tests that are identified as RC, those proposed AD was prompted by a report
(4) For Group 2, SR airplanes: Inspect procedures and tests must be done to comply of fatigue cracking found in a certain
before exceeding 37,800 flight cycles or with this AD; any procedures or tests that are fuselage frame, which severed the inner
56,700 flight hours, whichever occurs first not identified as RC are recommended. Those chord and web. This proposed AD
since the first flight of the airplane. procedures and tests that are not identified
would require inspecting the fuselage
as RC may be deviated from using accepted
methods in accordance with the operator’s frame for existing repairs, repetitive
TABLE 1 TO PARAGRAPH (h) OF THIS maintenance or inspection program without inspections, and applicable repairs. We
AD—COMPLIANCE TIME LOWER obtaining approval of an AMOC, provided are proposing this AD to address the
THRESHOLDS the procedures and tests identified as RC can unsafe condition on these products.
be done and the airplane can be put back in DATES: We must receive comments on
Compliance time flight cycles (FC) or an airworthy condition. Any substitutions or
Applicable flight hours (FH), whichever occurs this proposed AD by September 11,
airplanes changes to procedures or tests identified as
first since first flight of the airplane 2017.
RC require approval of an AMOC.
Group 1, LR Not before exceeding 30,900 FC or ADDRESSES: You may send comments,
66,700 FH. (l) Related Information using the procedures found in 14 CFR
Group 1, SR Not before exceeding 28,700 FC or (1) Refer to Mandatory Continuing 11.43 and 11.45, by any of the following
43,000 FH. Airworthiness Information (MCAI) EASA
Group 2, LR Not before exceeding 28,600 FC or methods:
61,700 FH.
Airworthiness Directive 2017–0023, dated • Federal eRulemaking Portal: Go to
Group 2, SR Not before exceeding 34,400 FC or February 10, 2017, for related information. http://www.regulations.gov. Follow the
51,600 FH. This MCAI may be found in the AD docket instructions for submitting comments.
on the Internet at http://www.regulations.gov
• Fax: 202–493–2251.
by searching for and locating Docket No.
(i) Service Information Exception
FAA–2017–0710.
• Mail: U.S. Department of
Where Airbus Service Bulletin A300–57– Transportation, Docket Operations, M–
(2) For more information about this AD,
6118, Revision 01, dated January 31, 2017, 30, West Building Ground Floor, Room
contact Dan Rodina, Aerospace Engineer,
specifies to contact Airbus for appropriate W12–140, 1200 New Jersey Avenue SE.,
International Branch, ANM–116, Transport
action, and specifies that action as ‘‘RC’’ Washington, DC 20590.
Airplane Directorate, FAA, 1601 Lind
(Required for Compliance): Before further
flight, accomplish corrective actions in
Avenue SW., Renton, WA 98057–3356; • Hand Delivery: Deliver to Mail
accordance with the procedures specified in telephone 425–227–2125; fax 425–227–1149. address above between 9 a.m. and 5
paragraph (k)(2) of this AD. (3) For service information identified in p.m., Monday through Friday, except
this AD, contact Airbus SAS, Airworthiness Federal holidays.
(j) Credit for Previous Actions Office—EAW, 1 Rond Point Maurice For service information identified in
mstockstill on DSK30JT082PROD with PROPOSALS
This paragraph provides credit for actions Bellonte, 31707 Blagnac Cedex, France; this NPRM, contact Boeing Commercial
required by paragraph (h) of this AD, if those telephone +33 5 61 93 36 96; fax +33 5 61
Airplanes, Attention: Contractual & Data
actions were performed before the effective 93 44 51; email account.airworth-eas@
airbus.com; Internet http://www.airbus.com.
Services (C&DS), 2600 Westminster
date of this AD using Airbus Service Bulletin
You may view this service information at the Blvd., MC 110–SK57, Seal Beach, CA
A300–57–6118, dated June 30, 2015.
FAA, Transport Airplane Directorate, 1601 90740; telephone: 562–797–1717;
(k) Other FAA AD Provisions Lind Avenue SW., Renton, WA. For Internet: https://
The following provisions also apply to this information on the availability of this www.myboeingfleet.com. You may view
AD: material at the FAA, call 425–227–1221. this referenced service information at
VerDate Sep<11>2014 17:09 Jul 26, 2017 Jkt 241001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\27JYP1.SGM 27JYP1](https://thefederalregister.org/doc/82_FR_35028/page/4.svg)
Document Created: 2017-07-27 02:06:58
Document Modified: 2017-07-27 02:06:58
| 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 September 11, 2017. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 82 FR 34885 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR