81 FR 10465 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 40 (March 1, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 40 (March 1, 2016)
| Page Range | 10465-10468 | |
| FR Document | 2016-04035 |
[Federal Register Volume 81, Number 40 (Tuesday, March 1, 2016)] [Rules and Regulations] [Pages 10465-10468] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-04035] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2455; Directorate Identifier 2014-NM-180-AD; Amendment 39-18415; AD 2016-04-21] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2008-26-07 for 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, 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 required repetitive inspections of the lower skin and stringers at certain stations, and corrective actions if necessary. This new AD continues to require the actions specified in AD 2008-26-07 and also requires 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. 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. DATES: This AD is effective April 5, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 5, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of January 28, 2009 (73 FR 78946, December 24, 2008). ADDRESSES: For service information identified in this 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), (``AD 2008-26-07''). AD 2008-26-07 applied 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. The NPRM published in the Federal Register on July 2, 2015 (80 FR 38038) (``the NPRM''). The NPRM was prompted by certain mandated programs intended to support the airplane reaching its limit of validity of [[Page 10466]] the engineering data that support the established structural maintenance program. The NPRM proposed to continue to require the actions specified in AD 2008-26-07 and also to 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; and corrective actions if necessary. 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. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response to the comment. Request To Clarify the Actions in Paragraph (j)(1) of the Proposed AD Boeing requested that we clarify paragraph (j)(1) of the proposed AD. Boeing stated that paragraph (j)(1) of the proposed AD does not specify what to inspect or how to inspect. Boeing recommended that a description similar to that of paragraph (j)(2) of the proposed AD be included in paragraph (j)(1) of the proposed AD. We agree with the request to clarify the inspection requirements. Paragraph (j)(l) of the AD is for airplanes that have previous structural repairs at the lower skins, stringers, and splice. For those airplanes, because the details of the configuration are not known, a specific description of the area to be inspected cannot be given. Paragraph (j)(2) of this AD provides specific inspections for certain airplanes because those inspections are described in Boeing Service Bulletin DC8-57-104, dated August 18, 2014. However, that service information does not provide specific inspection areas for airplanes identified in paragraph (j)(1) of this AD. Therefore, for the inspection and applicable corrective actions, paragraph (j)(1) of this AD requires that the operator use a method approved in the accordance with the procedures specified in paragraph (m) of this AD. We have revised paragraph (j)(1) of this AD to specify the general inspection area, which includes the lower skins, stringers, and splice fittings. Clarification of Actions Specified in Paragraph (k) of This AD. Paragraph (k) of the NPRM referred to Boeing Service Bulletin DC8- 57-104, dated August 18, 2014, for the compliance times for the actions required by that paragraph but did not include a reference for the installation and inspections required by paragraph (k) of this AD. We have revised paragraph (k) of this AD to refer to Boeing Service Bulletin DC8-57-104, dated August 18, 2014, as the appropriate source of service information for accomplishing the installation and inspections. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. 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. Costs of Compliance We estimate that this AD affects 12 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspection [retained actions from 6 work-hours x $85 $0 $510 $6,120 per inspection AD 2008[dash]26[dash]07, per hour = $510 per cycle. Amendment 39-15773 (73 FR 78946, inspection cycle. December 24, 2008)]. ETHF Inspection [new action]...... 8 work-hours x $85 $0 $680 $8,160 per inspection per 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 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. ---------------------------------------------------------------------------------------------------------------- [[Page 10467]] 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 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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: 2016-04-21 The Boeing Company: Amendment 39-18415; Docket No. FAA- 2015-2455; Directorate Identifier 2014-NM-180-AD. (a) Effective Date This AD is effective April 5, 2016. (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 Air Transport Association (ATA) of America Code 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 With No Changes This paragraph restates the requirements of paragraph (f) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), with no changes. 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 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 With No Changes This paragraph restates the exception specified in paragraph (g) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), with no changes. 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 With No Changes This paragraph restates the exception specified in paragraph (h) of AD 2008-26-07, Amendment 39-15773 (73 FR 78946, December 24, 2008), with no changes. 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 identified in Boeing Service Bulletin DC8-57-104, dated August 18, 2014: 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 of the lower skins, stringers, and splice fittings, 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 identified in Boeing Service Bulletin DC8-57-104, dated August 18, 2014: 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., [[Page 10468]] ``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, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC8-57-104, dated August 18, 2014. 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) 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) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (n) Related Information 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]. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on April 5, 2016. (i) Boeing Service Bulletin DC8-57-104, dated August 18, 2014. (ii) Reserved. (4) The following service information was approved for IBR on January 28, 2009 (73 FR 78946, December 24, 2008). (i) Boeing Alert Service Bulletin DC8-57A102, dated February 12, 2008. (ii) Reserved. (5) For Boeing service information identified in this 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. (6) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on February 15, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-04035 Filed 2-29-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Rules and Regulations 10465
having P/N MA20A1001–1 (S343T003–39) DEPARTMENT OF TRANSPORTATION & Services Management, 3855
for the fuel tanks is installed: Within 60 Lakewood Boulevard, MC D800–0019,
months after the effective date of this AD, Federal Aviation Administration Long Beach, CA 90846–0001; telephone
replace the affected MOV actuator with a 206–544–5000, extension 2; fax 206–
serviceable, FAA-approved MOV actuator 14 CFR Part 39 766–5683; Internet https://
other than one having P/N MA20A1001–1 www.myboeingfleet.com. You may view
(S343T003–39). [Docket No. FAA–2015–2455; Directorate
Identifier 2014–NM–180–AD; Amendment this referenced service information at
Note 1 to paragraph (h) of this AD: 39–18415; AD 2016–04–21] the FAA, Transport Airplane
Guidance on replacing the affected MOV Directorate, 1601 Lind Avenue SW.,
actuator may be found in the Boeing 767 RIN 2120–AA64
Renton, WA. For information on the
Aircraft Maintenance Manual or the Boeing availability of this material at the FAA,
777 Aircraft Maintenance Manual, as Airworthiness Directives; The Boeing
Company Airplanes call 425–227–1221. It is also available
applicable. on the Internet at http://
(i) Parts Installation Prohibition
AGENCY: Federal Aviation www.regulations.gov by searching for
Administration (FAA), DOT. and locating Docket No. FAA–2015–
As of the effective date of this AD, no 2455.
ACTION: Final rule.
person may install an MOV actuator having
P/N MA20A1001–1 (S343T003–39) on any SUMMARY: We are superseding Examining the AD Docket
airplane. Airworthiness Directive (AD) 2008–26– You may examine the AD docket on
(j) Alternative Methods of Compliance 07 for all The Boeing Company Model the Internet at http://
(AMOCs) DC–8–11, DC–8–12, DC–8–21, DC–8–31, www.regulations.gov by searching for
(1) The Manager, Seattle Aircraft DC–8–32, DC–8–33, DC–8–41, DC–8–42, and locating Docket No. FAA–2015–
Certification Office (ACO), FAA, has the and DC–8–43 airplanes; Model DC–8–50 2455; or in person at the Docket
authority to approve AMOCs for this AD, if series airplanes; Model DC–8F–54 and Management Facility between 9 a.m.
requested using the procedures found in 14 DC–8F–55 airplanes; Model DC–8–60 and 5 p.m., Monday through Friday,
CFR 39.19. In accordance with 14 CFR 39.19, series airplanes; Model DC–8–60F series except Federal holidays. The AD docket
send your request to your principal inspector airplanes; Model DC–8–70 series contains this AD, the regulatory
or local Flight Standards District Office, as airplanes; and Model DC–8–70F series evaluation, any comments received, and
appropriate. If sending information directly airplanes. AD 2008–26–07 required other information. The address for the
to the manager of the ACO, send it to the repetitive inspections of the lower skin Docket Office (phone: 800–647–5527) is
attention of the person identified in and stringers at certain stations, and Document Management Facility, U.S.
paragraph (k) of this AD. Information may be corrective actions if necessary. This new Department of Transportation, Docket
emailed to: 9-ANM-Seattle-ACO-AMOC- AD continues to require the actions Operations, M–30, West Building
Requests@faa.gov. specified in AD 2008–26–07 and also Ground Floor, Room W12–140, 1200
(2) Before using any approved AMOC, requires an eddy current high frequency New Jersey Avenue SE., Washington,
notify your appropriate principal inspector, (ETHF) inspection for cracks of the DC 20590.
or lacking a principal inspector, the manager fastener open holes common to the FOR FURTHER INFORMATION CONTACT:
of the local flight standards district office/ lower skins, stringers, and splice fittings Chandra Ramdoss, Aerospace Engineer,
certificate holding district office. at a certain station; installation of Airframe Branch, ANM–120L, FAA, Los
(k) Related Information external doublers and fasteners and Angeles Aircraft Certification Office
repetitive eddy current low frequency (ACO), 3960 Paramount Boulevard,
(1) For more information about this AD,
(ETLF) inspections around the fasteners Lakewood, CA 90712–4137; telephone:
contact Rebel Nichols, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
for any crack; and corrective actions if 562–627–5239; fax: 562–627–5210;
ACO, 1601 Lind Avenue SW., Renton, WA necessary. This AD was prompted by email: Chandraduth.Ramdoss@faa.gov.
98057–3356; phone: 425–917–6509; fax: 425– certain mandated programs intended to
SUPPLEMENTARY INFORMATION:
917–6590; email: rebel.nichols@faa.gov. support the airplane reaching its limit of
(2) For service information identified in validity of the engineering data that Discussion
this AD, contact Boeing Commercial support the established structural We issued a notice of proposed
Airplanes, Attention: Data & Services maintenance program. We are issuing rulemaking (NPRM) to amend 14 CFR
Management, P.O. Box 3707, MC 2H–65, this AD to detect and correct cracks in part 39 to supersede AD 2008–26–07,
Seattle, WA 98124–2207; telephone 206– the lower skins, stringers, and fastener Amendment 39–15773 (73 FR 78946,
544–5000, extension 1; fax 206–766–5680; holes of the splice fittings, which could December 24, 2008), (‘‘AD 2008–26–
Internet https://www.myboeingfleet.com. You result in the loss of structural integrity 07’’). AD 2008–26–07 applied to all
may view this referenced service information of the airplane. McDonnell Douglas Model DC–8–11,
at the FAA, Transport Airplane Directorate, DATES: This AD is effective April 5, DC–8–12, DC–8–21, DC–8–31, DC–8–32,
1601 Lind Avenue SW., Renton, WA. For 2016. DC–8–33, DC–8–41, DC–8–42, and DC–
information on the availability of this The Director of the Federal Register 8–43 airplanes; Model DC–8–50 series
material at the FAA, call 425–227–1221. approved the incorporation by reference airplanes; Model DC–8F–54 and DC–
(l) Material Incorporated by Reference of a certain publication listed in this AD 8F–55 airplanes; Model DC–8–60 series
None. as of April 5, 2016. airplanes; Model DC–8–60F series
asabaliauskas on DSK5VPTVN1PROD with RULES
The Director of the Federal Register airplanes; Model DC–8–70 series
Issued in Renton, Washington, on February approved the incorporation by reference airplanes; and Model DC–8–70F series
16, 2016. of a certain other publication listed in airplanes. The NPRM published in the
Michael Kaszycki, this AD as of January 28, 2009 (73 FR Federal Register on July 2, 2015 (80 FR
Acting Manager, Transport Airplane 78946, December 24, 2008). 38038) (‘‘the NPRM’’). The NPRM was
Directorate, Aircraft Certification Service. ADDRESSES: For service information prompted by certain mandated
[FR Doc. 2016–04033 Filed 2–29–16; 8:45 am] identified in this AD, contact Boeing programs intended to support the
BILLING CODE 4910–13–P Commercial Airplanes, Attention: Data airplane reaching its limit of validity of
VerDate Sep<11>2014 18:20 Feb 29, 2016 Jkt 238001 PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 E:\FR\FM\01MRR1.SGM 01MRR1](https://thefederalregister.org/doc/81_FR_10505/page/1.svg)
![10466 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Rules and Regulations
the engineering data that support the configuration are not known, a specific public interest require adopting this AD
established structural maintenance description of the area to be inspected with the changes described previously
program. The NPRM proposed to cannot be given. Paragraph (j)(2) of this and minor editorial changes. We have
continue to require the actions specified AD provides specific inspections for determined that these minor changes:
in AD 2008–26–07 and also to require certain airplanes because those • Are consistent with the intent that
an ETHF inspection for cracks of the inspections are described in Boeing was proposed in the NPRM for
fastener open holes common to the Service Bulletin DC8–57–104, dated correcting the unsafe condition; and
lower skins, stringers, and splice fittings August 18, 2014. However, that service
at a certain station; installation of information does not provide specific • Do not add any additional burden
external doublers and fasteners and inspection areas for airplanes identified upon the public than was already
repetitive ETLF inspections around the in paragraph (j)(1) of this AD. Therefore, proposed in the NPRM.
fasteners for any crack; and corrective for the inspection and applicable We also determined that these
actions if necessary. We are issuing this corrective actions, paragraph (j)(1) of changes will not increase the economic
AD to detect and correct cracks in the this AD requires that the operator use a burden on any operator or increase the
lower skins, stringers, and fastener holes method approved in the accordance scope of this AD.
of the splice fittings, which could result with the procedures specified in
in the loss of structural integrity of the paragraph (m) of this AD. We have Related Service Information Under 1
airplane. revised paragraph (j)(1) of this AD to CFR Part 51
Comments specify the general inspection area, We reviewed Boeing Service Bulletin
which includes the lower skins, DC8–57–104, dated August 18, 2014.
We gave the public the opportunity to stringers, and splice fittings.
participate in developing this AD. The The service information describes
following presents the comment Clarification of Actions Specified in procedures for certain airplanes for an
received on the NPRM and the FAA’s Paragraph (k) of This AD. ETHF inspection for cracks of the
response to the comment. fastener open holes common to the
Paragraph (k) of the NPRM referred to lower skins, stringers, and splice fittings
Request To Clarify the Actions in Boeing Service Bulletin DC8–57–104, at a certain station; installation of
Paragraph (j)(1) of the Proposed AD dated August 18, 2014, for the external doublers and fasteners and
Boeing requested that we clarify compliance times for the actions repetitive ETLF inspections around the
paragraph (j)(1) of the proposed AD. required by that paragraph but did not fasteners for any crack; and corrective
Boeing stated that paragraph (j)(1) of the include a reference for the installation actions. This service information is
proposed AD does not specify what to and inspections required by paragraph reasonably available because the
inspect or how to inspect. Boeing (k) of this AD. We have revised interested parties have access to it
recommended that a description similar paragraph (k) of this AD to refer to through their normal course of business
to that of paragraph (j)(2) of the Boeing Service Bulletin DC8–57–104, or by the means identified in the
proposed AD be included in paragraph dated August 18, 2014, as the
ADDRESSES section.
(j)(1) of the proposed AD. appropriate source of service
We agree with the request to clarify information for accomplishing the Costs of Compliance
the inspection requirements. Paragraph installation and inspections.
(j)(l) of the AD is for airplanes that have We estimate that this AD affects 12
Conclusion airplanes of U.S. registry.
previous structural repairs at the lower
skins, stringers, and splice. For those We reviewed the relevant data and We estimate the following costs to
airplanes, because the details of the determined that air safety and the comply with this AD:
ESTIMATED COSTS
Cost per prod-
Action Labor cost Parts cost Cost on U.S. operators
uct
Inspection [retained actions from AD 2008-26-07, 6 work-hours × $85 per $0 $510 $6,120 per inspection
Amendment 39–15773 (73 FR 78946, December hour = $510 per inspec- cycle.
24, 2008)]. tion cycle.
ETHF Inspection [new action] .................................... 8 work-hours × $85 per $0 $680 $8,160 per inspection
hour = $680 per inspec- cycle.
tion cycle.
We estimate the following costs to do that would be required based on the way of determining the number of
any necessary certain follow-on actions results of the inspection. We have no aircraft that might need these actions:
ON-CONDITION COSTS
asabaliauskas on DSK5VPTVN1PROD with RULES
Action Labor cost Parts cost Cost per product
Installation of External Doubler ................................................. 5 work-hour × $85 per hour = $20,000 $20,425.
$425.
Repetitive ETLF inspection ....................................................... 8 work-hour × $85 per hour = $0 $680 per inspection cycle.
$680 per inspection cycle.
VerDate Sep<11>2014 18:20 Feb 29, 2016 Jkt 238001 PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 E:\FR\FM\01MRR1.SGM 01MRR1](https://thefederalregister.org/doc/81_FR_10505/page/2.svg)
![Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Rules and Regulations 10467
For all actions and repairs on Groups PART 39—AIRWORTHINESS corrective actions before further flight.
1–3, Configuration 1 Airplanes, we have DIRECTIVES Thereafter, repeat the inspections at the
received no definitive data that would applicable intervals specified in paragraph
■ 1. The authority citation for part 39 1.E., ‘‘Compliance,’’ of Boeing Alert Service
enable us to provide cost estimates for Bulletin DC8–57A102, dated February 12,
the on-condition actions specified in continues to read as follows:
2008, until paragraph (j) of this AD is done.
this AD. Authority: 49 U.S.C. 106(g), 40113, 44701.
(h) Retained Exception for Compliance Time
Authority for this Rulemaking § 39.13 [Amended] With No Changes
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by This paragraph restates the exception
specifies the FAA’s authority to issue removing Airworthiness Directive (AD) specified in paragraph (g) of AD 2008–26–07,
Amendment 39–15773 (73 FR 78946,
rules on aviation safety. Subtitle I, 2008–26–07, Amendment 39–15773 (73 December 24, 2008), with no changes. Where
Section 106, describes the authority of FR 78946, December 24, 2008), and Boeing Alert Service Bulletin DC8–57A102,
the FAA Administrator. Subtitle VII, adding the following new AD: dated February 12, 2008, specifies a
Aviation Programs, describes in more 2016–04–21 The Boeing Company: compliance time ‘‘after the date on this
detail the scope of the Agency’s Amendment 39–18415; Docket No. service bulletin,’’ this AD requires
authority. FAA–2015–2455; Directorate Identifier compliance within the specified compliance
2014–NM–180–AD. time after January 28, 2009 (the effective date
We are issuing this rulemaking under
of AD 2008–26–07).
the authority described in Subtitle VII, (a) Effective Date
Part A, Subpart III, Section 44701, (i) Retained Exception for Corrective Action
This AD is effective April 5, 2016.
‘‘General requirements.’’ Under that With No Changes
section, Congress charges the FAA with (b) Affected ADs This paragraph restates the exception
promoting safe flight of civil aircraft in This AD replaces AD 2008–26–07, specified in paragraph (h) of AD 2008–26–07,
air commerce by prescribing regulations Amendment 39–15773 (73 FR 78946, Amendment 39–15773 (73 FR 78946,
for practices, methods, and procedures December 24, 2008). December 24, 2008), with no changes. If any
cracking is found during any inspection
the Administrator finds necessary for (c) Applicability required by paragraph (g) of this AD, and
safety in air commerce. This regulation This AD applies to all The Boeing Boeing Alert Service Bulletin DC8–57A102,
is within the scope of that authority Company Model DC–8–11, DC–8–12, DC–8– dated February 12, 2008, specifies to contact
because it addresses an unsafe condition 21, DC–8–31, DC–8–32, DC–8–33, DC–8–41, Boeing for appropriate action: Before further
that is likely to exist or develop on DC–8–42, DC–8–43, DC–8–51, DC–8–52, DC– flight, repair the cracking using a method
products identified in this rulemaking 8–53, DC–8–55, DC–8F–54, DC–8F–55, DC– approved in accordance with the procedures
action. 8–61, DC–8–62, DC–8–63, DC–8–61F, DC–8– specified in paragraph (m) of this AD.
62F, DC–8–63F, DC–8–71, DC–8–72, DC–8–
Regulatory Findings 73, DC–8–71F, DC–8–72F, and DC–8–73F (j) New Inspections and Corrective Action
airplanes; certificated in any category. (1) For Groups 1–3, Configuration 1
We have determined that this AD will airplanes identified in Boeing Service
not have federalism implications under (d) Subject Bulletin DC8–57–104, dated August 18, 2014:
Executive Order 13132. This AD will Air Transport Association (ATA) of At the applicable time specified in paragraph
not have a substantial direct effect on America Code 57, Wings. 1.E., ‘‘Compliance,’’ of Boeing Service
the States, on the relationship between Bulletin DC8–57–104, dated August 18, 2014,
(e) Unsafe Condition except as required in paragraph (l) of this AD,
the national government and the States, This AD was prompted by certain do an inspection for any cracking of the
or on the distribution of power and mandated programs intended to support the lower skins, stringers, and splice fittings, and
responsibilities among the various airplane reaching its limit of validity of the do all applicable corrective actions, using a
levels of government. engineering data that support the established method approved in accordance with the
For the reasons discussed above, I structural maintenance program. We are procedures specified in paragraph (m) of this
certify that this AD: issuing this AD to detect and correct cracks AD.
in the lower skins, stringers, and fastener (2) For Groups 1–3, Configuration 2
(1) Is not a ‘‘significant regulatory holes of the splice fittings, which could airplanes identified in Boeing Service
action’’ under Executive Order 12866, result in the loss of structural integrity of the Bulletin DC8–57–104, dated August 18, 2014:
(2) Is not a ‘‘significant rule’’ under airplane. At the applicable time specified in paragraph
DOT Regulatory Policies and Procedures 1.E., ‘‘Compliance,’’ of Boeing Service
(f) Compliance
(44 FR 11034, February 26, 1979), Bulletin DC8–57–104, dated August 18, 2014,
Comply with this AD within the except as required in paragraph (l) of this AD,
(3) Will not affect intrastate aviation compliance times specified, unless already do an eddy current high frequency (ETHF)
in Alaska, and done. inspection for any cracking of the fastener
(4) Will not have a significant (g) Retained Repetitive Inspections With No open holes common to the lower skins,
economic impact, positive or negative, stringers, and splice fittings at station Xw =
Changes
on a substantial number of small entities 408 and Xw = ¥408 from stringer 51 to
This paragraph restates the requirements of stringer 65, in accordance with the
under the criteria of the Regulatory paragraph (f) of AD 2008–26–07, Amendment Accomplishment Instructions of Boeing
Flexibility Act. 39–15773 (73 FR 78946, December 24, 2008), Service Bulletin DC8–57–104, dated August
List of Subjects in 14 CFR Part 39 with no changes. At the times specified in 18, 2014. If any cracking is found, before
paragraph 1.E., ‘‘Compliance,’’ of Boeing further flight, repair the crack using a method
Air transportation, Aircraft, Aviation Alert Service Bulletin DC8–57A102, dated approved in accordance with the procedures
asabaliauskas on DSK5VPTVN1PROD with RULES
safety, Incorporation by reference, February 12, 2008, except as provided by specified in paragraph (m) of this AD.
Safety. paragraph (h) of this AD, do the applicable
inspections for fatigue cracking of the lower (k) New Doubler and Fastener Installation
Adoption of the Amendment skin and stringers at stations Xw = 408 and and Eddy Current Low Frequency (ETLF)
Xw = ¥408, and do all applicable corrective Inspection of the External Doubler and
Accordingly, under the authority actions, by accomplishing all applicable Corrective Action
delegated to me by the Administrator, actions specified in the Accomplishment If no crack is found during the inspection
the FAA amends 14 CFR part 39 as Instructions of Boeing Alert Service Bulletin required by paragraph (j)(2) of this AD: At the
follows: DC8–57A102, dated February 12, 2008. Do all applicable times specified in paragraph 1.E.,
VerDate Sep<11>2014 18:20 Feb 29, 2016 Jkt 238001 PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 E:\FR\FM\01MRR1.SGM 01MRR1](https://thefederalregister.org/doc/81_FR_10505/page/3.svg)
![10468 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Rules and Regulations
‘‘Compliance,’’ of Boeing Service Bulletin approval of an AMOC, provided the RC steps, DEPARTMENT OF TRANSPORTATION
DC8–57–104, dated August 18, 2014, install including substeps and identified figures, can
external doublers and fasteners, and do an still be done as specified, and the airplane Federal Aviation Administration
external doubler ETLF inspection around the can be put back in an airworthy condition.
fasteners for any cracking, in accordance 14 CFR Part 39
with the Accomplishment Instructions of (n) Related Information
Boeing Service Bulletin DC8–57–104, dated For more information about this AD,
August 18, 2014. Repeat the external ETLF [Docket No. FAA–2015–1270; Directorate
contact Chandra Ramdoss, Aerospace
inspection at the applicable intervals Identifier 2014–NM–222–AD; Amendment
Engineer, Airframe Branch, ANM–120L, 39–18412; AD 2016–04–18]
specified in 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin DC8–57–104, dated August FAA, Los Angeles ACO, 3960 Paramount
18, 2014. If any cracking is found during any Boulevard, Lakewood, CA 90712–4137;
telephone: 562–627–5239; fax: 562–627– RIN 2120–AA64
ETLF inspection required by this paragraph,
before further flight, repair the crack using a 5210; email: Chandraduth.Ramdos@faa.gov.
Airworthiness Directives; The Boeing
method approved in accordance with the
procedures specified in paragraph (m) of this
(o) Material Incorporated by Reference Company Airplanes
AD. (1) The Director of the Federal Register AGENCY: Federal Aviation
approved the incorporation by reference
(l) Exception to the Compliance Time Administration (FAA), DOT.
(IBR) of the service information listed in this
Where Boeing Service Bulletin DC8–57– paragraph under 5 U.S.C. 552(a) and 1 CFR ACTION: Final rule.
104, dated August 18, 2014, specifies a part 51.
compliance time ‘‘after the original issue date SUMMARY: We are adopting a new
(2) You must use this service information
of this service bulletin,’’ this AD requires airworthiness directive (AD) for certain
compliance within the specified compliance as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
The Boeing Company Model 747–100,
time after the effective date of this AD. –200B, –200C, –200F, –300, –400,
(3) The following service information was
(m) Alternative Methods of Compliance approved for IBR on April 5, 2016.
–400D, and –400F series airplanes. This
(AMOCs) (i) Boeing Service Bulletin DC8–57–104, AD was prompted by reports of
(1) The Manager, Los Angeles Aircraft dated August 18, 2014. significant fuselage skin damage at
Certification Office (ACO), FAA, has the (ii) Reserved. certain parts of the dorsal fairing, due to
authority to approve AMOCs for this AD, if (4) The following service information was wear from the dorsal fairing. This AD
requested using the procedures found in 14 approved for IBR on January 28, 2009 (73 FR requires repetitive detailed inspections
CFR 39.19. In accordance with 14 CFR 39.19, for wear and cracks of the fuselage skin
78946, December 24, 2008).
send your request to your principal inspector under the dorsal fairing, and related
or local Flight Standards District Office, as (i) Boeing Alert Service Bulletin DC8–
57A102, dated February 12, 2008. investigative and corrective actions if
appropriate. If sending information directly
to the manager of the ACO, send it to the (ii) Reserved. necessary. This AD also requires
attention of the person identified in (5) For Boeing service information repetitive post-repair external surface
paragraph (n) of this AD. Information may be identified in this AD, contact Boeing high frequency eddy current inspections
emailed to 9-ANM-LAACO-AMOC- Commercial Airplanes, Attention: Data & of the blended areas of the skin and
REQUESTS@faa.gov. Services Management, 3855 Lakewood detailed inspections of the unrepaired
(2) Before using any approved AMOC, Boulevard, MC D800–0019, Long Beach, CA areas, and related investigative and
notify your appropriate principal inspector, 90846–0001; telephone 206–544–5000, corrective actions if necessary. We are
or lacking a principal inspector, the manager extension 2; fax 206–766–5683; Internet issuing this AD to detect and correct
of the local flight standards district office/ fuselage skin damage of the dorsal
https://www.myboeingfleet.com.
certificate holding district office.
(3) An AMOC that provides an acceptable (6) You may view this service information fairing area, which could result in skin
level of safety may be used for any repair at the FAA, Transport Airplane Directorate, cracking and consequent
required by this AD if it is approved by the 1601 Lind Avenue SW., Renton, WA. For depressurization of the airplane.
Boeing Commercial Airplanes Organization information on the availability of this DATES: This AD is effective April 5,
Designation Authorization (ODA) that has material at the FAA, call 425–227–1221. 2016.
been authorized by the Manager, Los Angeles (7) You may view this service information The Director of the Federal Register
ACO, to make those findings. For a repair that is incorporated by reference at the
method to be approved, the repair must meet
approved the incorporation by reference
National Archives and Records of a certain publication listed in this AD
the certification basis of the airplane, and the Administration (NARA). For information on
approval must specifically refer to this AD. as of April 5, 2016.
the availability of this material at NARA, call
(4) AMOCs approved for AD 2008–26–07, ADDRESSES: For service information
202–741–6030, or go to: http://
Amendment 39–15773 (73 FR 78946, identified in this final rule, contact
www.archives.gov/federal-register/cfr/ibr-
December 24, 2008), are approved as AMOCs Boeing Commercial Airplanes,
for the corresponding provisions of this AD. locations.html.
Attention: Data & Services Management,
(5) Except as required by paragraphs (j) and Issued in Renton, Washington, on February
(k) of this AD: For service information that
P.O. Box 3707, MC 2H–65, Seattle, WA
15, 2016. 98124–2207; telephone 206–544–5000,
contains steps that are labeled as Required
for Compliance (RC), the provisions of Michael Kaszycki, extension 1; fax 206–766–5680; Internet
paragraphs (m)(5)(i) and (m)(5)(ii) of this AD Acting Manager, Transport Airplane https://www.myboeingfleet.com. You
apply. Directorate, Aircraft Certification Service. may view this referenced service
(i) The steps labeled as RC, including [FR Doc. 2016–04035 Filed 2–29–16; 8:45 am] information at the FAA, Transport
asabaliauskas on DSK5VPTVN1PROD with RULES
substeps under an RC step and any figures BILLING CODE 4910–13–P Airplane Directorate, 1601 Lind Avenue
identified in an RC step, must be done to SW., Renton, WA. For information on
comply with the AD. An AMOC is required the availability of this material at the
for any deviations to RC steps, including
substeps and identified figures.
FAA, call 425–227–1221. It is also
(ii) Steps not labeled as RC may be available on the Internet at http://
deviated from using accepted methods in www.regulations.gov by searching for
accordance with the operator’s maintenance and locating Docket No. FAA–2015–
or inspection program without obtaining 1270.
VerDate Sep<11>2014 18:20 Feb 29, 2016 Jkt 238001 PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 E:\FR\FM\01MRR1.SGM 01MRR1](https://thefederalregister.org/doc/81_FR_10505/page/4.svg)
Document Created: 2018-02-02 15:00:09
Document Modified: 2018-02-02 15:00:09
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective April 5, 2016. | |
| 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 | 81 FR 10465 | |
| 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