80 FR 38038 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 127 (July 2, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 127 (July 2, 2015)
| Page Range | 38038-38041 | |
| FR Document | 2015-16154 |
[Federal Register Volume 80, Number 127 (Thursday, July 2, 2015)] [Proposed Rules] [Pages 38038-38041] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-16154] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2455; Directorate Identifier 2014-NM-180-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 supersede Airworthiness Directive (AD) 2008-26- 07, which applies to all McDonnell Douglas Model DC-8-11, DC-8-12, DC- 8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-50 series airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-60 series airplanes; Model DC-8-60F series airplanes; Model DC-8-70 series airplanes; and Model DC-8-70F series airplanes. AD 2008-26-07 currently requires repetitive inspections of the lower skin and stringers at certain stations, and corrective actions if necessary. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would also require an eddy current high frequency (ETHF) inspection for cracks of the fastener open holes common to the lower skins, stringers, and splice fittings at a certain station; installation of external doublers and fasteners and repetitive eddy current low frequency (ETLF) inspections around the fasteners for any crack; and corrective actions if necessary. We are proposing this AD to detect and correct cracks in the lower skins, stringers, and fastener holes of the splice fittings, which could result in the loss of structural integrity of the airplane. DATES: We must receive comments on this proposed AD by August 17, 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, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 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-2015-2455. 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- 2455; 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: Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: 562-627-5239; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2455; Directorate Identifier 2014-NM-180-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 On December 12, 2008, we issued AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), for all McDonnell Douglas Model DC-8- 11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-50 series airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-60 series airplanes; Model DC-8-60F series airplanes; Model DC-8-70 series airplanes; and Model DC-8-70F series airplanes. AD 2008-26-07 requires repetitive inspections of the lower skin and stringers at stations Xw=408 and Xw=-408, and corrective actions if [[Page 38039]] necessary. AD 2008-26-07 resulted from reports of cracks in the skins and stringers at the end fasteners common to the stringer end fittings at stations Xw=408 and Xw=-408 wing splice joints. We issued AD 2008- 26-07 to detect and correct fatigue cracking in the skins and stringers at the end fasteners common to the stringer end fittings at certain station and wing splice joints, which could result in wing structure that might not sustain limit load, and consequent loss of structural integrity of the wing. Widespread Fatigue Damage As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs have been developed to support initiatives that will ensure the continued airworthiness of aging airplane structure. The last element of those initiatives is the requirement to establish a limit of validity (LOV) of the engineering data that support the structural maintenance program under 14 CFR 26.21. This proposed AD is the result of an assessment of the previously established programs by Boeing during the process of establishing the LOV for The Boeing Company Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-50 series airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-60 series airplanes; Model DC-8-60F series airplanes; Model DC-8-70 series airplanes; and Model DC-8-70F series airplanes. The actions specified in this proposed AD are necessary to complete certain programs to ensure the continued airworthiness of aging airplane structure and to support an airplane reaching its LOV. We are proposing this AD to detect and correct cracks in the lower skins, stringers, and fastener holes of the splice fittings, which could result in the loss of structural integrity of the airplane. Actions Since AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008) Was Issued Since we issued AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), we have received new service information to ensure the continued airworthiness of aging airplane structure and to support an airplane reaching its LOV. The new inspection and modification of the left and right lower wing skin, stringers, and splice fittings will support operation up to the DC-8 LOV. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin DC8-57-104, dated August 18, 2014. The service information describes procedures for certain airplanes for an ETHF inspection for cracks of the fastener open holes common to the lower skins, stringers, and splice fittings at a certain station; installation of external doublers and fasteners and repetitive ETLF inspections around the fasteners for any crack; and corrective actions. 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 retain all requirements of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008). This proposed AD would also require an ETHF inspection for cracks of the fastener open holes common to the lower skins, stringers, and splice fittings at a certain station; installation of external doublers and fasteners and repetitive ETLF inspections around the fasteners for any crack if necessary; and corrective actions. Clarification of Actions for Groups 1-3, Configuration 1 Airplanes Where the Accomplishment Instructions of Boeing Service Bulletin DC8-57-104, dated August 18, 2014, specifies repair, this AD also requires an inspection and possible other actions. Change to AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008) Since AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), was issued, the AD format has been revised, and certain paragraphs have been rearranged with new title headers. As a result, the corresponding paragraph identifiers have been redesignated in this proposed AD, as listed in the following table: Revised Paragraph Identifiers ------------------------------------------------------------------------ Corresponding requirement in Requirement in AD 2008-26-07 this proposed AD ------------------------------------------------------------------------ paragraph (e)............................. paragraph (f) paragraph (f)............................. paragraph (g) paragraph (g)............................. paragraph (h) paragraph (h)............................. paragraph (i) ------------------------------------------------------------------------ Explanation of ``RC'' Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service 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. Costs of Compliance We estimate that this proposed AD affects 12 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: [[Page 38040]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost Action Labor cost Parts per Cost on U.S. operators cost product ---------------------------------------------------------------------------------------------------------------- Inspection [retained actions from AD 6 work-hours x $85 per $0 $510 $6,120 per inspection 2008[dash]26[dash]07, Amendment 39- hour = $510 per cycle 15773 (73 FR 78946, December 24, inspection cycle. 2008)]. ETHF Inspection [new proposed action].. 8 work-hours x $85 per $0 $680 $8,160 per inspection hour = $680 per cycle inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary certain follow- on actions that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these actions: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Installation of External Doubler......... 5 work-hour x $85 per hour $20,000 $20,425 = $425. Repetitive ETLF inspection............... 8 work-hour x $85 per hour $0 $680 per inspection cycle = $680 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- For all actions and repairs on Groups 1-3, Configuration 1 Airplanes, 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 have 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 that the 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 removing Airworthiness Directive (AD) 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), and adding the following new AD: The Boeing Company: Docket No. FAA-2015-2455; Directorate Identifier 2014-NM-180-AD. (a) Comments Due Date The FAA must receive comments on this AD action by August 17, 2015. (b) Affected ADs This AD replaces AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008). (c) Applicability This AD applies to all The Boeing Company Model DC-8-11, DC-8- 12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-61, DC- 8-62, DC-8-63, DC-8-61F, DC-8-62F, DC-8-63F, DC-8-71, DC-8-72, DC-8- 73, DC-8-71F, DC-8-72F, and DC-8-73F airplanes; certificated in any category. (d) Subject Joint Aircraft System Component (JASC) 57, Wings. (e) Unsafe Condition This AD was prompted by certain mandated programs intended to support the airplane reaching its limit of validity of the engineering data that support the established structural maintenance program. We are issuing this AD to detect and correct cracks in the lower skins, stringers, and fastener holes of the splice fittings, which could result in the loss of structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections This paragraph restates the requirements of paragraph (f) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008). At the times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, except as provided by paragraph (h) of this AD, do the applicable inspections for fatigue cracking of the lower skin and stringers at stations Xw=408 and Xw=-408, and do all applicable corrective actions, by accomplishing all applicable actions [[Page 38041]] specified in the Accomplishment Instructions of Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008. Do all corrective actions before further flight. Thereafter, repeat the inspections at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, until paragraph (j) of this AD is done. (h) Retained Exception for Compliance Time This paragraph restates the exception specified in paragraph (g) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008). Where Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008, specifies a compliance time ``after the date on this service bulletin,'' this AD requires compliance within the specified compliance time after January 28, 2009 (the effective date of AD 2008-26-07). (i) Retained Exception for Corrective Action This paragraph restates the exception specified in paragraph (h) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008): If any cracking is found during any inspection required by paragraph (g) of this AD, and Boeing Alert Service Bulletin DC8- 57A102, dated February 12, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (j) New Inspections and Corrective Action (1) For Groups 1-3, Configuration 1 Airplanes: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin DC8-57-104, dated August 18, 2014, except as required in paragraph (l) of this AD, do an inspection for any cracking, and do all applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (2) For Groups 1-3, Configuration 2 Airplanes: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin DC8-57-104, dated August 18, 2014, except as required in paragraph (l) of this AD, do an eddy current high frequency (ETHF) inspection for any cracking of the fastener open holes common to the lower skins, stringers, and splice fittings at station Xw=408 and Xw=-408 from stringer 51 to stringer 65, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-57-104, dated August 18, 2014. If any cracking is found, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (k) New Doubler and Fastener Installation and Eddy Current Low Frequency (ETLF) Inspection of the External Doubler and Corrective Action If no crack is found during the inspection required by paragraph (j)(2) of this AD: At the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin DC8-57-104, dated August 18, 2014, install external doublers and fasteners, and do an external doubler ETLF inspection around the fasteners for any cracking. Repeat the external ETLF inspection at the applicable intervals specified in 1.E., ``Compliance,'' of Boeing Service Bulletin DC8-57-104, dated August 18, 2014. If any cracking is found during any ETLF inspection required by this paragraph, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Exception to the Compliance Time Where Boeing Service Bulletin DC8-57-104, dated August 18, 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. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 (n)(1) of this AD. Information may be emailed to [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles 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) AMOCs approved for AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), are approved as AMOCs for the corresponding provisions of this AD. (5) Except as required by paragraphs (j) and (k) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(5)(i) and (m)(5)(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. (n) Related Information (1) For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: 562- 627-5239; fax: 562-627-5210; email: [email protected]. (2) For service information identified in this AD, Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 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. 2015-16154 Filed 7-1-15; 8:45 am] BILLING CODE 4910-13-P
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actions from a manufacturer, the action must airplanes; Model DC–8–60F series Examining the AD Docket
be accomplished using a method approved airplanes; Model DC–8–70 series
by the Manager, International Branch, ANM– You may examine the AD docket on
airplanes; and Model DC–8–70F series the Internet at http://
116, Transport Airplane Directorate, FAA; or airplanes. AD 2008–26–07 currently
the European Aviation Safety Agency www.regulations.gov by searching for
(EASA); or Airbus’s EASA Design
requires repetitive inspections of the and locating Docket No. FAA–2015–
Organization Approval (DOA). If approved by lower skin and stringers at certain 2455; or in person at the Docket
the DOA, the approval must include the stations, and corrective actions if Management Facility between 9 a.m.
DOA-authorized signature. necessary. This proposed AD is and 5 p.m., Monday through Friday,
intended to complete certain mandated except Federal holidays. The AD docket
(k) Related Information
programs intended to support the contains this proposed AD, the
(1) Refer to Mandatory Continuing airplane reaching its limit of validity
Airworthiness Information (MCAI) EASA regulatory evaluation, any comments
(LOV) of the engineering data that received, and other information. The
Airworthiness Directive 2014–0276, dated
December 19, 2014, for related information.
support the established structural street address for the Docket Office
This MCAI may be found in the AD docket maintenance program. This proposed (phone: 800–647–5527) is in the
on the Internet at http://www.regulations.gov AD would also require an eddy current ADDRESSES section. Comments will be
by searching for and locating Docket No. high frequency (ETHF) inspection for available in the AD docket shortly after
FAA–2015–1991. cracks of the fastener open holes receipt.
(2) For Airbus service information contact common to the lower skins, stringers,
Airbus, Airworthiness Office—EIAS, 1 Rond FOR FURTHER INFORMATION CONTACT:
and splice fittings at a certain station;
Point Maurice Bellonte, 31707 Blagnac Chandra Ramdoss, Aerospace Engineer,
installation of external doublers and
Cedex, France; telephone: +33 5 61 93 36 96; Airframe Branch, ANM–120L, FAA, Los
fasteners and repetitive eddy current
fax: +33 5 61 93 44 51; email: Angeles Aircraft Certification Office
low frequency (ETLF) inspections
account.airworth-eas@airbus.com; Internet (ACO), 3960 Paramount Boulevard,
http://www.airbus.com. around the fasteners for any crack; and
Lakewood, CA 90712–4137; telephone:
(3) For Goodrich service information corrective actions if necessary. We are
562–627–5239; fax: 562–627–5210;
contact Goodrich Aerostructures, 850 Lagoon proposing this AD to detect and correct
email: Chandraduth.Ramdoss@faa.gov.
Drive, Chula Vista, California, 91910–2098; cracks in the lower skins, stringers, and
telephone: 619–691–2719; email: jan.lewis@ SUPPLEMENTARY INFORMATION:
fastener holes of the splice fittings,
goodrich.com; Internet: http:// which could result in the loss of Comments Invited
www.goodrich.com/TechPubs. structural integrity of the airplane.
(4) You may view this referenced service We invite you to send any written
information at the FAA, Transport Airplane DATES: We must receive comments on relevant data, views, or arguments about
Directorate, 1601 Lind Avenue SW., Renton, this proposed AD by August 17, 2015. this proposed AD. Send your comments
WA. For information on the availability of ADDRESSES: You may send comments, to an address listed under the
this material at the FAA, call 425–227–1221. ADDRESSES section. Include ‘‘Docket No.
using the procedures found in 14 CFR
Issued in Renton, Washington, on June 24, 11.43 and 11.45, by any of the following FAA–2015–2455; Directorate Identifier
2015. methods: 2014–NM–180–AD’’ at the beginning of
Dionne Palermo, • Federal eRulemaking Portal: Go to your comments. We specifically invite
Acting Manager, Transport Airplane http://www.regulations.gov. Follow the comments on the overall regulatory,
Directorate, Aircraft Certification Service. instructions for submitting comments. economic, environmental, and energy
[FR Doc. 2015–16165 Filed 7–1–15; 8:45 am] • Fax: 202–493–2251. aspects of this proposed AD. We will
consider all comments received by the
BILLING CODE 4910–13–P • Mail: U.S. Department of closing date and may amend this
Transportation, Docket Operations, M– proposed AD because of those
30, West Building Ground Floor, Room comments.
DEPARTMENT OF TRANSPORTATION W12–140, 1200 New Jersey Avenue SE., We will post all comments we
Federal Aviation Administration Washington, DC 20590. receive, without change, to http://
• Hand Delivery: Deliver to Mail www.regulations.gov, including any
14 CFR Part 39 address above between 9 a.m. and 5 personal information you provide. We
p.m., Monday through Friday, except will also post a report summarizing each
[Docket No. FAA–2015–2455; Directorate Federal holidays.
Identifier 2014–NM–180–AD] substantive verbal contact we receive
For service information identified in about this proposed AD.
RIN 2120–AA64 this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data Discussion
Airworthiness Directives; The Boeing & Services Management, 3855 On December 12, 2008, we issued AD
Company Airplanes Lakewood Boulevard, MC D800–0019, 2008–26–07, Amendment 39–15773 (73
AGENCY: Federal Aviation Long Beach, CA 90846–0001; telephone FR 78946, December 24, 2008), for all
Administration (FAA), DOT. 206–544–5000, extension 2; fax 206– McDonnell Douglas Model DC–8–11,
ACTION: Notice of proposed rulemaking 766–5683; Internet https:// DC–8–12, DC–8–21, DC–8–31, DC–8–32,
(NPRM). www.myboeingfleet.com. You may view DC–8–33, DC–8–41, DC–8–42, and DC–
this referenced service information at 8–43 airplanes; Model DC–8–50 series
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
SUMMARY: We propose to supersede the FAA, Transport Airplane airplanes; Model DC–8F–54 and DC–
Airworthiness Directive (AD) 2008–26– Directorate, 1601 Lind Avenue SW., 8F–55 airplanes; Model DC–8–60 series
07, which applies to all McDonnell Renton, WA. For information on the airplanes; Model DC–8–60F series
Douglas Model DC–8–11, DC–8–12, DC– availability of this material at the FAA, airplanes; Model DC–8–70 series
8–21, DC–8–31, DC–8–32, DC–8–33, call 425–227–1221. It is also available airplanes; and Model DC–8–70F series
DC–8–41, DC–8–42, and DC–8–43 on the Internet at http:// airplanes. AD 2008–26–07 requires
airplanes; Model DC–8–50 series www.regulations.gov by searching for repetitive inspections of the lower skin
airplanes; Model DC–8F–54 and DC– and locating Docket No. FAA–2015– and stringers at stations Xw=408 and
8F–55 airplanes; Model DC–8–60 series 2455. Xw=-408, and corrective actions if
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ESTIMATED COSTS
Cost
Parts
Action Labor cost per Cost on U.S. operators
cost product
Inspection [retained actions from AD 6 work-hours × $85 per hour = $510 per inspec- $0 $510 $6,120 per inspection
2008-26-07, Amendment 39–15773 (73 FR tion cycle. cycle
78946, December 24, 2008)].
ETHF Inspection [new proposed action] ............. 8 work-hours × $85 per hour = $680 per inspec- $0 $680 $8,160 per inspection
tion cycle. cycle
We estimate the following costs to do that would be required based on the have no way of determining the number
any necessary certain follow-on actions results of the proposed inspection. We of aircraft that might need these actions:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Installation of External Doubler .............................. 5 work-hour × $85 per hour = $425 ....................... $20,000 $20,425
Repetitive ETLF inspection .................................... 8 work-hour × $85 per hour = $680 per inspection $0 $680 per inspection
cycle. cycle
For all actions and repairs on Groups (1) Is not a ‘‘significant regulatory (b) Affected ADs
1–3, Configuration 1 Airplanes, we have action’’ under Executive Order 12866, This AD replaces AD 2008–26–07,
received no definitive data that would (2) Is not a ‘‘significant rule’’ under Amendment 39–15773 (73 FR 78946,
enable us to provide cost estimates for the DOT Regulatory Policies and December 24, 2008).
the on-condition actions specified in Procedures (44 FR 11034, February 26, (c) Applicability
this proposed AD. 1979), This AD applies to all The Boeing
Authority for This Rulemaking (3) Will not affect intrastate aviation Company Model DC–8–11, DC–8–12, DC–8–
in Alaska, and 21, DC–8–31, DC–8–32, DC–8–33, DC–8–41,
Title 49 of the United States Code (4) Will not have a significant DC–8–42, DC–8–43, DC–8–51, DC–8–52, DC–
specifies the FAA’s authority to issue economic impact, positive or negative, 8–53, DC–8–55, DC–8F–54, DC–8F–55, DC–
rules on aviation safety. Subtitle I, on a substantial number of small entities 8–61, DC–8–62, DC–8–63, DC–8–61F, DC–8–
Section 106, describes the authority of under the criteria of the Regulatory
62F, DC–8–63F, DC–8–71, DC–8–72, DC–8–
the FAA Administrator. Subtitle VII, 73, DC–8–71F, DC–8–72F, and DC–8–73F
Flexibility Act. airplanes; certificated in any category.
Aviation Programs, describes in more
detail the scope of the Agency’s List of Subjects in 14 CFR Part 39 (d) Subject
authority. Air transportation, Aircraft, Aviation Joint Aircraft System Component (JASC)
We are issuing this rulemaking under 57, Wings.
safety, Incorporation by reference,
the authority described in Subtitle VII,
Safety. (e) Unsafe Condition
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that The Proposed Amendment This AD was prompted by certain
section, Congress charges the FAA with mandated programs intended to support the
Accordingly, under the authority airplane reaching its limit of validity of the
promoting safe flight of civil aircraft in
delegated to me by the Administrator, engineering data that support the established
air commerce by prescribing regulations
the FAA proposes to amend 14 CFR part structural maintenance program. We are
for practices, methods, and procedures issuing this AD to detect and correct cracks
39 as follows:
the Administrator finds necessary for in the lower skins, stringers, and fastener
safety in air commerce. This regulation PART 39—AIRWORTHINESS holes of the splice fittings, which could
is within the scope of that authority DIRECTIVES result in the loss of structural integrity of the
because it addresses an unsafe condition airplane.
that is likely to exist or develop on ■ 1. The authority citation for part 39 (f) Compliance
products identified in this rulemaking continues to read as follows: Comply with this AD within the
action. compliance times specified, unless already
Authority: 49 U.S.C. 106(g), 40113, 44701.
Regulatory Findings done.
§ 39.13 [Amended]
We have determined that this (g) Retained Repetitive Inspections
■ 2. The FAA amends § 39.13 by
proposed AD would not have federalism This paragraph restates the requirements of
removing Airworthiness Directive (AD) paragraph (f) of AD 2008–26–07, Amendment
implications under Executive Order
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
2008–26–07, Amendment 39–15773 (73 39–15773 (73 FR 78946, December 24, 2008).
13132. This proposed AD would not
FR 78946, December 24, 2008), and At the times specified in paragraph 1.E.,
have a substantial direct effect on the
adding the following new AD: ‘‘Compliance,’’ of Boeing Alert Service
States, on the relationship between the
The Boeing Company: Docket No. FAA– Bulletin DC8–57A102, dated February 12,
national Government and the States, or 2008, except as provided by paragraph (h) of
2015–2455; Directorate Identifier 2014–
on the distribution of power and NM–180–AD. this AD, do the applicable inspections for
responsibilities among the various fatigue cracking of the lower skin and
levels of government. (a) Comments Due Date stringers at stations Xw=408 and Xw=¥408,
For the reasons discussed above, I The FAA must receive comments on this and do all applicable corrective actions, by
certify that the proposed regulation: AD action by August 17, 2015. accomplishing all applicable actions
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![Federal Register / Vol. 80, No. 127 / Thursday, July 2, 2015 / Proposed Rules 38041
specified in the Accomplishment external ETLF inspection at the applicable Boulevard, Lakewood, CA 90712–4137;
Instructions of Boeing Alert Service Bulletin intervals specified in 1.E., ‘‘Compliance,’’ of telephone: 562–627–5239; fax: 562–627–
DC8–57A102, dated February 12, 2008. Do all Boeing Service Bulletin DC8–57–104, dated 5210; email: Chandraduth.Ramdos@faa.gov.
corrective actions before further flight. August 18, 2014. If any cracking is found (2) For service information identified in
Thereafter, repeat the inspections at the during any ETLF inspection required by this this AD, Boeing Commercial Airplanes,
applicable intervals specified in paragraph paragraph, before further flight, repair the Attention: Data & Services Management, 3855
1.E., ‘‘Compliance,’’ of Boeing Alert Service crack using a method approved in Lakewood Boulevard, MC D800–0019, Long
Bulletin DC8–57A102, dated February 12, accordance with the procedures specified in Beach, CA 90846–0001; telephone 206–544–
2008, until paragraph (j) of this AD is done. paragraph (m) of this AD. 5000, extension 2; fax 206–766–5683;
(l) Exception to the Compliance Time Internet https://www.myboeingfleet.com. You
(h) Retained Exception for Compliance Time
may view this referenced service information
This paragraph restates the exception Where Boeing Service Bulletin DC8–57– at the FAA, Transport Airplane Directorate,
specified in paragraph (g) of AD 2008–26–07, 104, dated August 18, 2014, specifies a 1601 Lind Avenue SW., Renton, WA. For
Amendment 39–15773 (73 FR 78946, compliance time ‘‘after the original issue date information on the availability of this
December 24, 2008). Where Boeing Alert of this service bulletin,’’ this AD requires material at the FAA, call 425–227–1221.
Service Bulletin DC8–57A102, dated compliance within the specified compliance
February 12, 2008, specifies a compliance time after the effective date of this AD. Issued in Renton, Washington, on June 24,
time ‘‘after the date on this service bulletin,’’ 2015.
(m) Alternative Methods of Compliance
this AD requires compliance within the Dionne Palermo,
(AMOCs)
specified compliance time after January 28, Acting Manager, Transport Airplane
2009 (the effective date of AD 2008–26–07). (1) The Manager, Los Angeles Aircraft Directorate, Aircraft Certification Service.
Certification Office (ACO), FAA, has the
(i) Retained Exception for Corrective Action authority to approve AMOCs for this AD, if [FR Doc. 2015–16154 Filed 7–1–15; 8:45 am]
This paragraph restates the exception requested using the procedures found in 14 BILLING CODE 4910–13–P
specified in paragraph (h) of AD 2008–26–07, CFR 39.19. In accordance with 14 CFR 39.19,
Amendment 39–15773 (73 FR 78946, send your request to your principal inspector
December 24, 2008): If any cracking is found or local Flight Standards District Office, as CONSUMER PRODUCT SAFETY
during any inspection required by paragraph appropriate. If sending information directly
to the manager of the ACO, send it to the
COMMISSION
(g) of this AD, and Boeing Alert Service
Bulletin DC8–57A102, dated February 12, attention of the person identified in
paragraph (n)(1) of this AD. Information may
16 CFR Parts 1112 and 1233
2008, specifies to contact Boeing for
appropriate action: Before further flight, be emailed to 9-ANM-LAACO-AMOC- [Docket No. CPSC–2015–0016]
repair the cracking using a method approved REQUESTS@faa.gov.
in accordance with the procedures specified (2) Before using any approved AMOC, Safety Standard for Portable Hook-On
in paragraph (m) of this AD. notify your appropriate principal inspector, Chairs
or lacking a principal inspector, the manager
(j) New Inspections and Corrective Action of the local flight standards district office/ AGENCY: Consumer Product Safety
(1) For Groups 1–3, Configuration 1 certificate holding district office. Commission.
Airplanes: At the applicable time specified in (3) An AMOC that provides an acceptable
ACTION: Notice of proposed rulemaking.
paragraph 1.E., ‘‘Compliance,’’ of Boeing level of safety may be used for any repair
Service Bulletin DC8–57–104, dated August required by this AD if it is approved by the
SUMMARY: The Danny Keysar Child
18, 2014, except as required in paragraph (l) Boeing Commercial Airplanes Organization
of this AD, do an inspection for any cracking, Designation Authorization (ODA) that has Product Safety Notification Act, section
and do all applicable corrective actions using been authorized by the Manager, Los Angeles 104 of the Consumer Product Safety
a method approved in accordance with the ACO, to make those findings. For a repair Improvement Act of 2008 (‘‘CPSIA’’),
procedures specified in paragraph (m) of this method to be approved, the repair must meet requires the United States Consumer
AD. the certification basis of the airplane, and the Product Safety Commission
(2) For Groups 1–3, Configuration 2 approval must specifically refer to this AD. (‘‘Commission’’ or ‘‘CPSC’’) to
Airplanes: At the applicable time specified in (4) AMOCs approved for AD 2008–26–07, promulgate consumer product safety
paragraph 1.E., ‘‘Compliance,’’ of Boeing Amendment 39–15773 (73 FR 78946,
standards for durable infant or toddler
Service Bulletin DC8–57–104, dated August December 24, 2008), are approved as AMOCs
18, 2014, except as required in paragraph (l) for the corresponding provisions of this AD. products. These standards are to be
of this AD, do an eddy current high (5) Except as required by paragraphs (j) and ‘‘substantially the same as’’ applicable
frequency (ETHF) inspection for any cracking (k) of this AD: For service information that voluntary standards or more stringent
of the fastener open holes common to the contains steps that are labeled as Required than the voluntary standard if the
lower skins, stringers, and splice fittings at for Compliance (RC), the provisions of Commission concludes that more
station Xw=408 and Xw=¥408 from stringer paragraphs (m)(5)(i) and (m)(5)(ii) apply. stringent requirements would further
51 to stringer 65, in accordance with the (i) The steps labeled as RC, including reduce the risk of injury associated with
Accomplishment Instructions of Boeing substeps under an RC step and any figures the product. The Commission is
Service Bulletin DC8–57–104, dated August identified in an RC step, must be done to
18, 2014. If any cracking is found, before comply with the AD. An AMOC is required proposing a safety standard for portable
further flight, repair the crack using a method for any deviations to RC steps, including hook-on chairs (‘‘hook-on chairs’’) in
approved in accordance with the procedures substeps and identified figures. response to the direction under section
specified in paragraph (m) of this AD. (ii) Steps not labeled as RC may be 104(b) of the CPSIA. In addition, the
(k) New Doubler and Fastener Installation
deviated from using accepted methods in Commission is proposing an
accordance with the operator’s maintenance amendment to include an additional
and Eddy Current Low Frequency (ETLF) or inspection program without obtaining
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Inspection of the External Doubler and CFR part in the list of notice of
approval of an AMOC, provided the RC steps, requirements (‘‘NORs’’) issued by the
Corrective Action including substeps and identified figures, can
If no crack is found during the inspection still be done as specified, and the airplane Commission.
required by paragraph (j)(2) of this AD: At the can be put back in an airworthy condition. DATES: Submit comments by September
applicable times specified in paragraph 1.E., 15, 2015.
‘‘Compliance,’’ of Boeing Service Bulletin (n) Related Information
DC8–57–104, dated August 18, 2014, install (1) For more information about this AD, ADDRESSES: Comments related to the
external doublers and fasteners, and do an contact Chandra Ramdoss, Aerospace Paperwork Reduction Act aspects of the
external doubler ETLF inspection around the Engineer, Airframe Branch, ANM–120L, marking, labeling, and instructional
fasteners for any cracking. Repeat the FAA, Los Angeles ACO, 3960 Paramount literature requirements of the proposed
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Document Created: 2015-12-15 13:15:17
Document Modified: 2015-12-15 13:15:17
| 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 17, 2015. | |
| Contact | Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: 562-627-5239; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 80 FR 38038 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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