Airworthiness Directives; The Boeing Company Airplanes, 70787-70790 [2014-26439]

Download as PDF Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Rules and Regulations PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2014–07–51, Amendment 39–17902 (79 FR 45329, August 5, 2014), and adding the following new AD: ■ 2014–24–02 Agusta S.p.A. (Agusta): Amendment 39–18035; Docket No. FAA– 2014–0971; Directorate Identifier 2014–SW– 055–AD. (a) Applicability This AD applies to Agusta Model AB139 and AW139 helicopters with main rotor (M/ R) rotating scissors part number (P/N) 3G6230A00733, with a lower half scissors spherical bearing (bearing) P/N 3G6230V00654 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as excessive play of the bearing in the M/R rotating scissors. This condition could result in failure of the M/R rotating scissors and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2014–07–51, Amendment 39–17902 (79 FR 45329, August 5, 2014). (d) Effective Date This AD becomes effective December 15, 2014. tkelley on DSK3SPTVN1PROD with RULES (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) For helicopters with the M/R rotating controls installed without special nut P/N 3G6230A06851, within 5 hours time-inservice (TIS), and thereafter before the first flight of each day or at intervals not exceeding 24 hours, whichever occurs later; and for helicopters with the M/R rotating controls installed with special nut P/N 3G6230A06851, within 25 hours TIS, and thereafter at intervals not exceeding 25 hours TIS: (i) Visually inspect the M/R rotating scissors for damage using a light source and a magnifying glass, paying particular attention to the bearings. Some examples of damage are shown in Figures 4 through 8 of AgustaWestland Bollettino Tecnico No. 139– 392, dated September 23, 2014 (BT 139–392). If there is damage, before further flight, remove the bearing. (ii) Inspect the M/R rotating scissors for play of each bearing, paying particular attention to the bearing staking condition, by manually moving the lower half scissor along the axis of the spherical bearing. Refer to VerDate Sep<11>2014 19:32 Nov 26, 2014 Jkt 235001 Figure 1 of BT 139–392. If there is play, before further flight, accomplish a detailed inspection of the M/R rotating scissors in accordance with steps 9.1 through 12.9 of AgustaWestland AW139 Document Code 39– C–62–31–00–00A–286C–A, Rotating control installation—Fixed swashplate and rotating scissors—Detailed inspection, issue 001, dated August 6, 2012. Any play beyond allowable limits requires removing the bearing before further flight. (2) Within 50 hours TIS from August 20, 2014, remove any bearing from a M/R rotating scissors with serial numbers (S/N) listed in Table 1 of AgustaWestland Bolletino Tecnico No. 139–368, dated March 19, 2014 (BT 139–368), on which the bearing has never been replaced; or from a M/R rotating scissors on which the bearing was replaced with a bearing with a S/N listed in Table 2 of BT 139–368. (3) Within 100 hours TIS, install special nut P/N 3G6230A06851 in accordance with steps 5.1. through 6., Part II, of the Compliance Instructions, of BT 139–392. (4) Prior to installing a M/R rotating scissors with a S/N listed in Table 1 of BT 139–368, replace the bearing and re-identify the M/R rotating scissors in accordance with paragraphs 4.2 through 4.4., Part II, of the Compliance Instructions of BT 139–368. (5) Do not install a bearing with a S/N listed in Table 2 of BT 139–368 into any M/ R rotating scissors. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222– 5110; email robert.grant@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (h) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) Emergency AD 2014–0215–E, dated September 24, 2014. You may view the EASA AD on the Internet at https:// www.regulations.gov by searching for and locating it in Docket No. FAA–2014–0971. (i) Subject Joint Aircraft Service Component (JASC) Code: 6200, M/R System. (j) 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. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 70787 (3) The following service information was approved for IBR on December 15, 2014. (i) AgustaWestland Bollettino Tecnico No. 139–392, dated September 23, 2014. (ii) Reserved. (4) The following service information was approved for IBR on August 20, 2014 (79 FR 45329, August 5, 2014). (i) AgustaWestland Bollettino Tecnico No. 139–368, dated March 19, 2014. (ii) AgustaWestland AW139 Document Code 39–C–62–31–00–00A–286C–A, Rotating control installation—Fixed swashplate and rotating scissors—Detailed inspection, issue 001, dated August 6, 2012. (5) For AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D’Angelo; telephone 39 0331–664757; fax 39 0331–664680; or at https:// www.agustawestland.com/technicalbulletins. (6) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on November 17, 2014. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–27995 Filed 11–26–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0235; Directorate Identifier 2013–NM–249–AD; Amendment 39–18015; AD 2014–22–10] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC–8–55, 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. This AD was prompted by multiple reports of cracking of the upper aft skin panel of SUMMARY: E:\FR\FM\28NOR1.SGM 28NOR1 70788 Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Rules and Regulations the fuselage. An evaluation by the design approval holder (DAH) indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage (WFD). This AD requires removing any previously installed local repairs; installing a full-length improvement modification with or without finger doublers, or a full-length repair with or without finger doublers, as applicable; and doing repetitive inspections for cracking of the doublers, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane. DATES: This AD is effective January 2, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 2, 2015. 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0235; 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: Chandraduth Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712–4137, phone: 562–627–5239; fax: 562–627– 5210; email: chandraduth.ramdoss@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model DC–8–55, 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 April 17, 2014 (79 FR 21648). The NPRM was prompted by multiple reports of cracking of the upper aft skin panel of the fuselage. An evaluation by the DAH indicates that the upper aft skin panel of the fuselage is subject to WFD. The NPRM proposed to require removing any previously installed local repairs; installing a fulllength improvement modification with finger doublers or a full-length repair with finger doublers; and doing repetitive inspections for cracking of the doublers, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane. Comment We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (79 FR 21648, April 17, 2014), and the FAA’s response to the comment. Request To Revise Repair or Modification Procedure Boeing requested that we revise paragraph (g) of the NPRM (79 FR 21648, April 17, 2014) to allow operators the option to repair or modify without finger doublers. Boeing also requested that we revise the inspection requirements of paragraph (h) of the NPRM to address the option to repair or modify without finger doublers. Boeing stated that the service rework drawing that is referenced in Boeing Alert Service Bulletin DC8–53A080, Revision 2, dated September 18, 2013, includes two repair and preventive modification configurations, depending on whether finger doublers will be installed. We agree with the commenter’s request to allow the procedure to repair or modify without finger doublers as an approved option for repair or modification. We have revised paragraphs (g) and (h)(1) of this final rule accordingly. Conclusion We reviewed the relevant data, considered the comment received, 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 (79 FR 21648, April 17, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 21648, April 17, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 18 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost tkelley on DSK3SPTVN1PROD with RULES Full-length modification or repair ............................................ Inspection ............................................................................... VerDate Sep<11>2014 19:32 Nov 26, 2014 Jkt 235001 PO 00000 Up to 184 work-hours × $85 Up to $14,720 per hour = $15,640. 9 work-hours × $85 per hour $0 ................... = $765 per inspection cycle. Frm 00018 Fmt 4700 Sfmt 4700 Cost per product Parts cost E:\FR\FM\28NOR1.SGM Up to $30,360 $765 per inspection cycle. 28NOR1 Cost on U.S. operators Up to $546,480. $13,770 per inspection cycle. Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Rules and Regulations We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701. 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 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. tkelley on DSK3SPTVN1PROD with RULES 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: VerDate Sep<11>2014 19:32 Nov 26, 2014 Jkt 235001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2014–22–10 The Boeing Company: Amendment 39–18015; Docket No. FAA–2014–0235; Directorate Identifier 2013–MN–249–AD. (a) Effective Date This AD is effective January 2, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company airplanes identified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, as identified in Boeing Alert Service Bulletin DC8–53A080, Revision 2, dated September 18, 2013. (1) The Boeing Company Model DC–8–55 airplanes. (2) The Boeing Company Model DC–8F–54 and DC–8F–55 airplanes. (3) The Boeing Company Model DC–8–61, DC–8–62, and DC–8–63 airplanes. (4) The Boeing Company Model DC–8–61F, DC–8–62F, and DC–8–63F airplanes. (5) The Boeing Company Model DC–8–71, DC–8–72, and DC–8–73 airplanes. (6) The Boeing Company Model DC–8–71F, DC–8–72F, and DC–8–73F airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by multiple reports of cracking of the upper aft skin panel of the fuselage. An evaluation by the design approval holder indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification or Repair Before the accumulation of 45,400 total flight cycles, or within 72 months after the effective date of this AD, whichever occurs later: Remove any previously installed local repairs and install a full-length improvement modification with or without finger doublers, or a full-length repair with or without finger doublers, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC8–53A080, Revision PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 70789 2, dated September 18, 2013. Installation of the full-length improvement modification or full-length repair, in accordance with paragraph (i) of AD 2008–06–23, Amendment 39–15435 (73 FR 14378, March 18, 2008), is a method of compliance with the requirements of this paragraph. Installation of a local repair as specified in paragraph (i) of AD 2008–06–23, does not comply with the requirements of this paragraph. (h) Post-Modification or Post-Repair Repetitive Inspections After accomplishing the actions required by paragraph (g) of this AD, at the applicable time and intervals specified in paragraph (h)(1) or (h)(2) of this AD: Do an external visual inspection or low frequency eddy current (LFEC) inspection for cracking along all four edges of each external doubler, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC8–53A080, Revision 2, dated September 18, 2013. Repeat the inspections thereafter at the applicable time and interval specified in paragraphs (h)(1) and (h)(2) of this AD. Accomplishment of the applicable repetitive inspection specified in paragraph (j)(1) or (j)(2)(ii) of AD 2008–06–23, Amendment 39– 15435 (73 FR 14378, March 18, 2008), is a method of compliance with the applicable inspection requirements of this paragraph. (1) For repair or modification with finger doublers: Within 30,000 flight cycles after doing the actions specified in paragraph (g) of this AD, do an external visual inspection. Repeat the external visual inspection thereafter at intervals not to exceed 5,000 flight cycles. (2) For repair or modification without finger doublers: Within 15,000 flight cycles after doing the actions specified in paragraph (g) of this AD, do a LFEC inspection. Repeat the LFEC inspection thereafter at intervals not to exceed 10,000 flight cycles. (i) Cracking Repair If any cracking is found during any inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin DC8–53A080, dated June 22, 2004; or Boeing Alert Service Bulletin DC8– 53A080, Revision 1, dated May 3, 2013. Boeing Alert Service Bulletin DC8–53A080, dated June 22, 2004, is incorporated by reference in AD 2008–06–23, Amendment 39–15435 (73 FR 14378, March 18, 2008). Boeing Alert Service Bulletin DC8–53A080, Revision 1, dated May 3, 2013, is not incorporated by reference in this AD. (k) 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, E:\FR\FM\28NOR1.SGM 28NOR1 70790 Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Rules and Regulations 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 (l)(1) of this AD. Information may be emailed to: 9–ANM–LAACO–AMOC– REQUESTS@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, 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 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. (l) Related Information (1) For more information about this AD, contact Chandraduth Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712–4137, phone: 562– 627–5239; fax: 562–627–5210; email: chandraduth.ramdoss@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD tkelley on DSK3SPTVN1PROD with RULES (m) 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. (i) Boeing Alert Service Bulletin DC8– 53A080, Revision 2, dated September 18, 2013. (ii) Reserved. (3) 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. (4) 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. (5) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Sep<11>2014 19:32 Nov 26, 2014 Jkt 235001 Issued in Renton, Washington, on October 28, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–26439 Filed 11–26–14; 8:45 am] BILLING CODE 4910–13–P FEDERAL COMMUNICATIONS COMMISSION 47 CFR Parts 1 and 20 [WT Docket No. 10–4; FCC 14–138] The Commission’s Rules To Improve Wireless Coverage Through the Use of Signal Boosters Federal Communications Commission. ACTION: Final rule; petition for reconsideration. AGENCY: In the Order on Reconsideration, the Commission addresses two Petitions for Reconsideration of the technical rules adopted in the Signal Boosters Report and Order, granting one petition and granting the other in part. DATES: Effective December 29, 2014, except for the revision to 47 CFR 20.21(f)(1)(iv)(A)(2), which contains information collection requirements subject to the Paperwork Reduction Act of 1995, Public Law 104–13, that are not effective until after approval by the Office of Management and Budget. The Federal Communications Commission will publish a document in the Federal Register announcing OMB approval and the effective date of this rule revision. FOR FURTHER INFORMATION CONTACT: Amanda Huetinck of the Mobility Division, Wireless Telecommunications Bureau, at (202) 418–7090 or Amanda.Huetinck@fcc.gov. For additional information concerning the Paperwork Reduction Act information collection requirements contained in this document, contact Cathy Williams at (202) 418–2918, or via the Internet at PRA@fcc.gov. SUPPLEMENTARY INFORMATION: This is the Federal Communications Commission’s Order on Reconsideration, in WT Docket No. 10–4, FCC 14–138, adopted September 19, 2014, and released September 23, 2014. The Further Notice of Proposed Rulemaking that was adopted concurrently with the Order on Reconsideration is published elsewhere in this issue of the Federal Register. The full text of that document is available for inspection and copying during normal business hours in the FCC Reference Center, 445 12th Street SUMMARY: PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 SW., Room CY–A257, Washington, DC 20554, or by downloading the text from the Commission’s Web site at https:// www.fcc.gov/document/signal-boostersorder-reconsideration-and-fnprm. The complete text also may be purchased from the Commission’s duplicating contractor, Best Copy and Printing, Inc., Portals II, 445 12th Street SW., Suite CY–B402, Washington, DC 20554. Alternative formats are available for people with disabilities (Braille, large print, electronic files, audio format), by sending an email to FCC504@fcc.gov or calling the Consumer and Government Affairs Bureau at (202) 418–0530 (voice), (202) 418–0432 (TTY). Synopsis I. Introduction and Background 1. In the Order on Reconsideration, we address two Petitions for Reconsideration of the technical rules adopted in the Signal Boosters Report and Order. 2. As discussed below, we grant the Wi-Ex Petition and amend certain technical rules for Wideband Consumer Signal Boosters. These amendments will streamline the testing procedures for Wideband Consumer Signal Boosters and will benefit consumers by decreasing the costs and complexities associated with the manufacture and certification of such devices. We also grant in part, to the extent described below, and otherwise deny the Verizon Petition and amend certain technical rules for mobile Provider-Specific Consumer Signal Boosters. These amendments will ensure consumers have access to a wide variety of signal boosters while strengthening the technical protections for wireless networks. II. Order on Reconsideration A. Background 3. Report and Order. On February 20, 2013, the Commission adopted a new regulatory framework to allow consumers to realize the benefits of using signal boosters while preventing, controlling, and, if necessary, resolving interference to wireless networks. In the Report and Order, the Commission adopted new technical, operational, and registration requirements for signal boosters. The new rules created two classes of signal boosters—Consumer and Industrial—with distinct regulatory requirements for each. For Consumer Signal Boosters, the Commission adopted a Network Protection Standard (NPS)—a flexible set of requirements for the design and manufacture of Consumer Signal Boosters, which are intended to couple signal booster E:\FR\FM\28NOR1.SGM 28NOR1

Agencies

[Federal Register Volume 79, Number 229 (Friday, November 28, 2014)]
[Rules and Regulations]
[Pages 70787-70790]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26439]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0235; Directorate Identifier 2013-NM-249-AD; 
Amendment 39-18015; AD 2014-22-10]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model DC-8-55, 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. This AD 
was prompted by multiple reports of cracking of the upper aft skin 
panel of

[[Page 70788]]

the fuselage. An evaluation by the design approval holder (DAH) 
indicates that the upper aft skin panel of the fuselage is subject to 
widespread fatigue damage (WFD). This AD requires removing any 
previously installed local repairs; installing a full-length 
improvement modification with or without finger doublers, or a full-
length repair with or without finger doublers, as applicable; and doing 
repetitive inspections for cracking of the doublers, and repair if 
necessary. We are issuing this AD to detect and correct fatigue 
cracking of the upper aft skin panel of the fuselage, which could 
result in loss of structural integrity and consequent rapid 
decompression of the airplane.

DATES: This AD is effective January 2, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 2, 
2015.

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0235; 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: Chandraduth Ramdoss, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, 
CA 90712-4137, phone: 562-627-5239; fax: 562-627-5210; email: 
chandraduth.ramdoss@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model DC-8-55, 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 April 17, 2014 (79 FR 21648). The NPRM was 
prompted by multiple reports of cracking of the upper aft skin panel of 
the fuselage. An evaluation by the DAH indicates that the upper aft 
skin panel of the fuselage is subject to WFD. The NPRM proposed to 
require removing any previously installed local repairs; installing a 
full-length improvement modification with finger doublers or a full-
length repair with finger doublers; and doing repetitive inspections 
for cracking of the doublers, and repair if necessary. We are issuing 
this AD to detect and correct fatigue cracking of the upper aft skin 
panel of the fuselage, which could result in loss of structural 
integrity and consequent rapid decompression of the airplane.

Comment

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (79 FR 
21648, April 17, 2014), and the FAA's response to the comment.

Request To Revise Repair or Modification Procedure

    Boeing requested that we revise paragraph (g) of the NPRM (79 FR 
21648, April 17, 2014) to allow operators the option to repair or 
modify without finger doublers. Boeing also requested that we revise 
the inspection requirements of paragraph (h) of the NPRM to address the 
option to repair or modify without finger doublers. Boeing stated that 
the service rework drawing that is referenced in Boeing Alert Service 
Bulletin DC8-53A080, Revision 2, dated September 18, 2013, includes two 
repair and preventive modification configurations, depending on whether 
finger doublers will be installed.
    We agree with the commenter's request to allow the procedure to 
repair or modify without finger doublers as an approved option for 
repair or modification. We have revised paragraphs (g) and (h)(1) of 
this final rule accordingly.

Conclusion

    We reviewed the relevant data, considered the comment received, 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:
     [Agr]re consistent with the intent that was proposed in 
the NPRM (79 FR 21648, April 17, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 21648, April 17, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 18 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on  U.S.
             Action                   Labor cost          Parts cost       Cost per  product       operators
----------------------------------------------------------------------------------------------------------------
Full-length modification or       Up to 184           Up to $14,720.....  Up to $30,360.....  Up to $546,480.
 repair.                           work[dash]hours x
                                   $85 per hour =
                                   $15,640.
Inspection......................  9 work-hours x $85  $0................  $765 per            $13,770 per
                                   per hour = $765                         inspection cycle.   inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 70789]]

    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

    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 adding the following new airworthiness 
directive (AD):

2014-22-10 The Boeing Company: Amendment 39-18015; Docket No. FAA-
2014-0235; Directorate Identifier 2013-MN-249-AD.

(a) Effective Date

    This AD is effective January 2, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company airplanes identified in 
paragraphs (c)(1) through (c)(6) of this AD, certificated in any 
category, as identified in Boeing Alert Service Bulletin DC8-53A080, 
Revision 2, dated September 18, 2013.
    (1) The Boeing Company Model DC-8-55 airplanes.
    (2) The Boeing Company Model DC-8F-54 and DC-8F-55 airplanes.
    (3) The Boeing Company Model DC-8-61, DC-8-62, and DC-8-63 
airplanes.
    (4) The Boeing Company Model DC-8-61F, DC-8-62F, and DC-8-63F 
airplanes.
    (5) The Boeing Company Model DC-8-71, DC-8-72, and DC-8-73 
airplanes.
    (6) The Boeing Company Model DC-8-71F, DC-8-72F, and DC-8-73F 
airplanes.

 (d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by multiple reports of cracking of the 
upper aft skin panel of the fuselage. An evaluation by the design 
approval holder indicates that the upper aft skin panel of the 
fuselage is subject to widespread fatigue damage. We are issuing 
this AD to detect and correct fatigue cracking of the upper aft skin 
panel of the fuselage, which could result in loss of structural 
integrity and consequent rapid decompression of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Modification or Repair

    Before the accumulation of 45,400 total flight cycles, or within 
72 months after the effective date of this AD, whichever occurs 
later: Remove any previously installed local repairs and install a 
full-length improvement modification with or without finger 
doublers, or a full-length repair with or without finger doublers, 
as applicable, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated 
September 18, 2013. Installation of the full-length improvement 
modification or full-length repair, in accordance with paragraph (i) 
of AD 2008-06-23, Amendment 39-15435 (73 FR 14378, March 18, 2008), 
is a method of compliance with the requirements of this paragraph. 
Installation of a local repair as specified in paragraph (i) of AD 
2008-06-23, does not comply with the requirements of this paragraph.

(h) Post-Modification or Post-Repair Repetitive Inspections

    After accomplishing the actions required by paragraph (g) of 
this AD, at the applicable time and intervals specified in paragraph 
(h)(1) or (h)(2) of this AD: Do an external visual inspection or low 
frequency eddy current (LFEC) inspection for cracking along all four 
edges of each external doubler, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC8-
53A080, Revision 2, dated September 18, 2013. Repeat the inspections 
thereafter at the applicable time and interval specified in 
paragraphs (h)(1) and (h)(2) of this AD. Accomplishment of the 
applicable repetitive inspection specified in paragraph (j)(1) or 
(j)(2)(ii) of AD 2008-06-23, Amendment 39-15435 (73 FR 14378, March 
18, 2008), is a method of compliance with the applicable inspection 
requirements of this paragraph.
    (1) For repair or modification with finger doublers: Within 
30,000 flight cycles after doing the actions specified in paragraph 
(g) of this AD, do an external visual inspection. Repeat the 
external visual inspection thereafter at intervals not to exceed 
5,000 flight cycles.
    (2) For repair or modification without finger doublers: Within 
15,000 flight cycles after doing the actions specified in paragraph 
(g) of this AD, do a LFEC inspection. Repeat the LFEC inspection 
thereafter at intervals not to exceed 10,000 flight cycles.

(i) Cracking Repair

    If any cracking is found during any inspection required by 
paragraph (h) of this AD: Before further flight, repair using a 
method approved in accordance with the procedures specified in 
paragraph (k) of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin DC8-53A080, dated June 22, 2004; or Boeing Alert Service 
Bulletin DC8-53A080, Revision 1, dated May 3, 2013. Boeing Alert 
Service Bulletin DC8-53A080, dated June 22, 2004, is incorporated by 
reference in AD 2008-06-23, Amendment 39-15435 (73 FR 14378, March 
18, 2008). Boeing Alert Service Bulletin DC8-53A080, Revision 1, 
dated May 3, 2013, is not incorporated by reference in this AD.

(k) 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,

[[Page 70790]]

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 (l)(1) of this AD. Information may be 
emailed to: 9-ANM-LAACO-AMOC-REQUESTS@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, 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 14 CFR 25.571, 
Amendment 45, and the approval must specifically refer to this AD.

(l) Related Information

    (1) For more information about this AD, contact Chandraduth 
Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., 
Suite 100, Lakewood, CA 90712-4137, phone: 562-627-5239; fax: 562-
627-5210; email: chandraduth.ramdoss@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD

(m) 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.
    (i) Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated 
September 18, 2013.
    (ii) Reserved.
    (3) 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.
    (4) 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.
    (5) 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on October 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-26439 Filed 11-26-14; 8:45 am]
BILLING CODE 4910-13-P
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