80 FR 43940 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 142 (July 24, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 142 (July 24, 2015)
| Page Range | 43940-43944 | |
| FR Document | 2015-17978 |
[Federal Register Volume 80, Number 142 (Friday, July 24, 2015)] [Rules and Regulations] [Pages 43940-43944] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-17978] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-1052; Directorate Identifier 2014-NM-140-AD; Amendment 39-18210; AD 2015-15-01] 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) 2004-13-02, which applied to certain The Boeing Company Model 747-100, -200B, and - 200F series airplanes. AD 2004-13-02 required repetitive inspections to find discrepancies in the upper and lower skins of the fuselage lap joints, and repair if necessary. This new AD adds post-repair inspections for cracking and corrosion, and repair if necessary; structural modification at the lap joints; and post-modification inspections for cracking and corrosion, and repair if necessary. This AD was prompted by an evaluation by the design approval holder (DAH) that indicates the longitudinal lap joints are subject to widespread fatigue damage (WFD). The actions mandated by this AD are necessary to reach the limit of validity (LOV). We are issuing this AD to detect and correct fatigue cracking in the upper and lower skins of the fuselage lap joints, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. [[Page 43941]] DATES: This AD is effective August 28, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 28, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014- 1052. 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-2014- 1052; 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 Docket 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: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2004-13-02, Amendment 39-13682 (69 FR 35237, June 24, 2004). AD 2004-13-02 applied to certain The Boeing Company Model 747-100, -200B, and -200F series airplanes. The NPRM published in the Federal Register on January 23, 2015 (80 FR 3506). The NPRM was prompted by an evaluation by the DAH that indicates the longitudinal lap joints are subject to WFD. A structural modification at the lap joint, and post-modification repetitive inspections of the skin, existing internal doubler, or splice strap for cracks, and corrective actions if necessary, are necessary to reach the limit of validity (LOV). The NPRM proposed to continue to require repetitive inspections to find discrepancies in the upper and lower skins of the fuselage lap joints, and repair if necessary; and to add post-repair inspections for cracking and corrosion, and repair if necessary; structural modification at the lap joints; and post-modification inspections for cracking and corrosion, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in the upper and lower skins of the fuselage lap joints, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 3506, January 23, 2015) and the FAA's response to each comment. Support for the NPRM (80 FR 3506, January 23, 2015) Boeing stated that it concurs with the content of the proposed rule (80 FR 3506, January 23, 2015). Request To Increase Inspection Frequency for Certain Airplanes An anonymous commenter expressed an opinion that there may be more reason to check airplanes that are frequently pressurized to a greater than 2.0 per-square-inch (psi) range than those that are not pressurized to that extent. The commenter also asked if there should be a weighted system that requires inspections sooner if an airplane has proportionally more flight cycles in the greater-than-, rather than the less-than, 2.0-psi differentials. We do not agree with the commenter's request for different inspection intervals based on pressurization ranges. The proposed inspection intervals were based on airplanes flying in a normal condition, which included full pressurization. In the past, if an operator had documentation substantiating flight cycles of less than 2.0 psi, some of the inspection requirements could be reduced. This reduced inspection requirement was relieving in nature and occurred roughly 10 years ago. We have since determined that fleet findings did not support this relief and have disallowed reduced inspection requirements in future ADs. We have not provided this relief in this AD. We have not changed this final rule in this regard. Request To Increase WFD Rule Applicability An anonymous commenter requested a reason why the WFD regulation applies only to Boeing and not to any other airplane manufacturer. The commenter stated that it seems like this type of WFD would be present in more than just Boeing airplanes, and yet the regulation and requirement for inspection seems to single out Boeing. The commenter suggested that it would make sense to consolidate and apply these requirements equally over all the types of airplanes. We do not agree with the commenter's request. On May 24, 2012, we made effective Amendment 26-6 of 14 CFR 26.21, ``Limit of Validity,'' of the Federal Aviation Regulations (14 CFR 26.21). This regulation required all design approval holders (DAHs) to develop an LOV for affected airplanes, which affected several manufacturers and models (not exclusively Boeing). The LOV is established by means of engineering data that support the structural maintenance program that corresponds to the period of time, stated as a number of total accumulated flight cycles or flight hours or both, during which it is demonstrated that WFD will not occur in the airplane. We have not changed this final rule in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 3506, January 23, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 3506, January 23, 2015). 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 Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014. The service information describes procedures for inspections and repairs of cracks and corrosion in the skin at lap joints in the fuselage. This service information is reasonably available because the [[Page 43942]] interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Costs of Compliance We estimate that this AD affects 2 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Parts Cost on U.S. Action Labor cost cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections [actions retained 5,628 work-hours x $85 $0 $478,380 per $956,760 per from AD 2004[dash]13[dash]02, per hour = $478,380 per inspection cycle. inspection cycle. Amendment 39[dash]13682 (69 FR inspection cycle. 35237, June 24, 2004)]. Modification [new action]........ Up to 3,764 $0 Up to $319,940...... Up to $639,880. work[dash]hours x $85 per hour = $319,940. Post-modification/ Up to 3,764 $0 Up to $319,940 per Up to $639,880 per post[dash]repair inspections work[dash]hours x $85 inspection cycle. inspection cycle. [new action]. per hour = $319,940 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- 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) 2004-13-02, Amendment 39-13682 (69 FR 35237, June 24, 2004), and adding the following new AD: 2015-15-01 The Boeing Company: Amendment 39-18210; Docket No. FAA- 2014-1052; Directorate Identifier 2014-NM-140-AD. (a) Effective Date This AD is effective August 28, 2015. (b) Affected ADs This AD replaces AD 2004-13-02, Amendment 39-13682 (69 FR 35237, June 24, 2004). (c) Applicability This AD applies to The Boeing Company Model 747-100, -200B, and -200F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) that indicates the longitudinal lap joints are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking in the upper and lower skins of the fuselage lap joints, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections for Corrosion, and Corrective Actions For airplanes identified as Groups 2 through 14 in Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014: Except as provided by paragraph (l)(3) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, do an external low frequency eddy current inspection for corrosion at the upper row of fasteners in the lap joint, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection at the upper row of fasteners in the lap joint thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(3) of this AD. Accomplishment of a structural modification in accordance with Part 5 of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD, terminates the inspection requirements of this paragraph in the area of the modification only. The actions required by paragraph (j) of this AD are still applicable in the area of the modification. (h) Inspections for Cracking, and Corrective Actions For airplanes identified as Groups 2 through 14 in Boeing Alert Service Bulletin [[Page 43943]] 747-53A2463, Revision 2, dated June 16, 2014: Except as provided by paragraph (l)(3) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, do an internal medium frequency eddy current inspection for skin cracks at the lower row of fasteners in the lap joint, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection at the lower row of fasteners in the lap joint thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(3) of this AD. Accomplishment of a structural modification in accordance with Part 5 of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD, terminates the inspection requirements of this paragraph in the area of the modification only. The actions required by paragraph (j) of this AD are still applicable in the area of the modification. (i) Structural Modification For airplanes identified as Groups 2 through 14 in Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(2) of this AD, do a structural modification at the lap joints, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD. Do all applicable corrective actions before further flight. Accomplishment of the structural modification required by this paragraph terminates the inspections required by paragraphs (g), (h), and (k) of this AD in the area of the modification only. The actions required by paragraph (j) of this AD are still applicable in the area of the modification. (j) Post-Modification Inspections and Corrective Actions For airplanes on which the actions required by paragraph (i) of this AD have been done: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(2) of this AD, do an internal high frequency eddy current (HFEC) inspection for cracks of the skin or existing internal doublers, and an open-hole HFEC inspection for splice strap cracks, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Repeat the inspections of the skin, internal doublers, and splice straps thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014. (k) Post-Repair Inspections and Corrective Actions For airplanes with any new or existing external doubler repair accomplished at a lap joint and the repair doubler length is 40 inches or longer: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(2) of this AD, do an internal HFEC inspection for cracking or corrosion of the repairs, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of external doubler repairs accomplished at lap joints thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014. Accomplishment of a structural modification in accordance with Part 5 of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD, terminates the inspection requirements of this paragraph in the area of the modification only. The actions required by paragraph (j) of this AD are still applicable in the area of the modification. (l) Exceptions (1) If, during any action required by this AD, Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, specifies to contact Boeing for an inspection or modification procedure, or repair instructions: Before further flight, do the inspection, or modification, or repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (2) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, specifies a compliance time ``after the Revision 2 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (3) For the compliance threshold and repetitive interval calculations for inspections required by paragraphs (g) and (h) of this AD, the provisions specified in paragraphs (l)(3)(i) and (l)(3)(ii) of this AD apply regarding differential pressure. (i) For inspections done before the effective date of this AD: Flight cycles in which the cabin differential pressure was at 2.0 pounds-per-square-inch (psi) or less need not be counted in the flight-cycle determination, provided that flight cycles with momentary spikes in cabin differential pressure above 2.0 psi were included as full pressure flight cycles. For this provision to apply, all cabin pressure records must have been maintained for each airplane. No fleet-averaging of cabin pressure is allowed. (ii) For inspections done on or after the effective date of this AD: All flight cycles must be counted, regardless of differential pressure. (m) 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 the service information identified in paragraph (m)(1) or (m)(2) of this AD. (1) Boeing Alert Service Bulletin 747-53A2463, dated March 7, 2002, including Appendices A, B, and C, dated March 7, 2002, which was incorporated by reference in AD 2004-13-02, Amendment 39-13682 (69 FR 35237, June 24, 2004). (2) Boeing Alert Service Bulletin 747-53A2463, Revision 1, dated April 16, 2009, which is not incorporated by reference in this AD. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (o)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2004-13-02, Amendment 39-13682 (69 FR 35237, June 24, 2004), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (o) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6432; fax: 425-917-6590; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p)(4) of this AD. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference [[Page 43944]] (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 747-53A2463, Revision 2, dated June 16, 2014. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on July 10, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-17978 Filed 7-23-15; 8:45 am] BILLING CODE 4910-13-P
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the FAA amends 14 CFR part 39 as (h) Modification of the SECU 855–7401; email thd.crj@
follows: Within 1,600 flight hours or 48 months aero.bombardier.com; Internet http://
after the effective date of this AD, whichever www.bombardier.com.
PART 39—AIRWORTHINESS occurs first: Modify and re-identify the (4) You may view this service information
DIRECTIVES SECU, in accordance with the at the FAA, Transport Airplane Directorate,
Accomplishment Instructions of Bombardier 1601 Lind Avenue SW., Renton, WA. For
■ 1. The authority citation for part 39 Service Bulletin 100–27–16, dated October information on the availability of this
continues to read as follows: 31, 2013. Doing the actions required by this material at the FAA, call 425–227–1221.
paragraph terminates the actions required by (5) You may view this service information
Authority: 49 U.S.C. 106(g), 40113, 44701. paragraph (g) of this AD. that is incorporated by reference at the
National Archives and Records
§ 39.13 [Amended] (i) Parts Installation Prohibition Administration (NARA). For information on
■ 2. The FAA amends § 39.13 by adding As of the effective date of this AD, no the availability of this material at NARA, call
the following new airworthiness person may install an SECU, P/N C47330– 202–741–6030, or go to: http://
directive (AD): 006, C47330–007, or C47330–008, on any www.archives.gov/federal-register/cfr/ibr-
airplane. locations.html.
AD 2015–15–08 Bombardier, Inc.:
Amendment 39–18217. Docket No. (j) Other FAA AD Provisions Issued in Renton, Washington, on July 15,
FAA–2015–0088; Directorate Identifier 2015.
The following provisions also apply to this
2014–NM–179–AD. Suzanne Masterson,
AD:
(a) Effective Date (1) Alternative Methods of Compliance Acting Manager, Transport Airplane
(AMOCs): The Manager, New York Aircraft Directorate, Aircraft Certification Service.
This AD becomes effective August 28,
Certification Office (ACO), ANE–170, FAA, [FR Doc. 2015–17937 Filed 7–23–15; 8:45 am]
2015.
has the authority to approve AMOCs for this BILLING CODE 4910–13–P
(b) Affected ADs AD, if requested using the procedures found
None. in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal DEPARTMENT OF TRANSPORTATION
(c) Applicability inspector or local Flight Standards District
This AD applies to Bombardier, Inc. Model Office, as appropriate. If sending information Federal Aviation Administration
BD–100–1A10 (Challenger 300) airplanes, directly to the ACO, send it to ATTN:
equipped with a spoiler electronic control Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart 14 CFR Part 39
unit (SECU) having part number (P/N)
C47330–006, C47330–007, or C47330–008; Avenue, Suite 410, Westbury, NY 11590; [Docket No. FAA–2014–1052; Directorate
certificated in any category. telephone 516–228–7300; fax 516–794–5531. Identifier 2014–NM–140–AD; Amendment
Before using any approved AMOC, notify 39–18210; AD 2015–15–01]
(d) Subject your appropriate principal inspector, or
Air Transport Association (ATA) of lacking a principal inspector, the manager of RIN 2120–AA64
America Code 27, Flight Controls. the local flight standards district office/
certificate holding district office. The AMOC Airworthiness Directives; The Boeing
(e) Reason approval letter must specifically reference Company Airplanes
This AD was prompted by testing of the this AD.
spoiler electronic control unit (SECU) (2) Contacting the Manufacturer: For any AGENCY: Federal Aviation
software for an upgrade, which revealed a requirement in this AD to obtain corrective Administration (FAA), DOT.
timing error between the command and actions from a manufacturer, the action must ACTION: Final rule.
monitor channels. We are issuing this AD to be accomplished using a method approved
prevent a timing error in the SECU software, by the Manager, New York ACO, ANE–170, SUMMARY: We are superseding
which, in combination with failure of the roll FAA; or TCCA; or Bombardier, Inc.’s TCCA Airworthiness Directive (AD) 2004–13–
disconnect switch, could result in complete DAO. If approved by the DAO, the approval 02, which applied to certain The Boeing
loss of spoiler functionality and consequent must include the DAO-authorized signature. Company Model 747–100, –200B, and
reduced controllability of the airplane.
(k) Related Information –200F series airplanes. AD 2004–13–02
(f) Compliance required repetitive inspections to find
Refer to Mandatory Continuing
Comply with this AD within the Airworthiness Information (MCAI) Canadian discrepancies in the upper and lower
compliance times specified, unless already Airworthiness Directive CF–2014–24, dated skins of the fuselage lap joints, and
done. August 5, 2014, for related information. This repair if necessary. This new AD adds
(g) Revision of the Maintenance or MCAI may be found in the AD docket on the post-repair inspections for cracking and
Inspection Program Internet at http://www.regulations.gov by corrosion, and repair if necessary;
searching for and locating it in Docket No. structural modification at the lap joints;
Within 600 flight hours since the most FAA–2015–0088–0002.
recent operational test of the aileron and post-modification inspections for
disconnect system for spoiler functionality as (l) Material Incorporated by Reference cracking and corrosion, and repair if
of the effective date of this AD, or within 400 (1) The Director of the Federal Register necessary. This AD was prompted by an
flight hours after the effective date of this AD, approved the incorporation by reference evaluation by the design approval
whichever occurs first: Revise the (IBR) of the service information listed in this holder (DAH) that indicates the
maintenance or inspection program, as paragraph under 5 U.S.C. 552(a) and 1 CFR longitudinal lap joints are subject to
applicable, to incorporate repetitive part 51. widespread fatigue damage (WFD). The
operational tests of the aileron disconnect (2) You must use this service information actions mandated by this AD are
system for spoiler functionality, and all as applicable to do the actions required by necessary to reach the limit of validity
applicable corrective actions, using a method this AD, unless this AD specifies otherwise. (LOV). We are issuing this AD to detect
rmajette on DSK2VPTVN1PROD with RULES
approved by the Manager, New York ACO, (i) Bombardier Service Bulletin 100–27–16,
ANE–170, FAA. and correct fatigue cracking in the upper
dated October 31, 2013.
Note 1 to paragraph (g) of this AD: (ii) Reserved. and lower skins of the fuselage lap
Guidance on operational tests of the aileron (3) For service information identified in joints, which could result in sudden
disconnect system can be found in the this AD, contact Bombardier, Inc., 400 Côte- fracture and failure of a lap joint and
Bombardier Inc., BD–100–1A10 Time Limits/ Vertu Road West, Dorval, Québec H4S 1Y9, rapid in-flight decompression of the
Maintenance Checks (TLMC) Manual. Canada; telephone 514–855–5000; fax 514– airplane fuselage.
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interested parties have access to it Costs of Compliance We estimate the following costs to
through their normal course of business comply with this AD:
or by the means identified in the We estimate that this AD affects 2
ADDRESSES section of this AD. airplanes of U.S. registry.
ESTIMATED COSTS
Parts Cost on U.S.
Action Labor cost Cost per product
cost operators
Inspections [actions retained from AD 5,628 work-hours × $85 per hour = $0 $478,380 per inspec- $956,760 per inspec-
2004-13-02, Amendment 39-13682 (69 $478,380 per inspection cycle. tion cycle. tion cycle.
FR 35237, June 24, 2004)].
Modification [new action] ............................. Up to 3,764 work-hours × $85 per hour = $0 Up to $319,940 ........ Up to $639,880.
$319,940.
Post-modification/post-repair inspections Up to 3,764 work-hours × $85 per hour = $0 Up to $319,940 per Up to $639,880 per
[new action]. $319,940 per inspection cycle. inspection cycle. inspection cycle.
We have received no definitive data on a substantial number of small entities (e) Unsafe Condition
that would enable us to provide cost under the criteria of the Regulatory This AD was prompted by an evaluation by
estimates for the on-condition actions Flexibility Act. the design approval holder (DAH) that
specified in this AD. indicates the longitudinal lap joints are
List of Subjects in 14 CFR Part 39 subject to widespread fatigue damage (WFD).
Authority for This Rulemaking We are issuing this AD to detect and correct
Air transportation, Aircraft, Aviation fatigue cracking in the upper and lower skins
Title 49 of the United States Code safety, Incorporation by reference, of the fuselage lap joints, which could result
specifies the FAA’s authority to issue Safety. in sudden fracture and failure of a lap joint
rules on aviation safety. Subtitle I, and rapid in-flight decompression of the
Section 106, describes the authority of Adoption of the Amendment airplane fuselage.
the FAA Administrator. Subtitle VII,
Accordingly, under the authority (f) Compliance
Aviation Programs, describes in more
delegated to me by the Administrator, Comply with this AD within the
detail the scope of the Agency’s
the FAA amends 14 CFR part 39 as compliance times specified, unless already
authority.
follows: done.
We are issuing this rulemaking under
the authority described in Subtitle VII, PART 39—AIRWORTHINESS (g) Inspections for Corrosion, and Corrective
Part A, Subpart III, Section 44701, Actions
DIRECTIVES
‘‘General requirements.’’ Under that For airplanes identified as Groups 2
section, Congress charges the FAA with through 14 in Boeing Alert Service Bulletin
■ 1. The authority citation for part 39 747–53A2463, Revision 2, dated June 16,
promoting safe flight of civil aircraft in continues to read as follows:
air commerce by prescribing regulations 2014: Except as provided by paragraph (l)(3)
Authority: 49 U.S.C. 106(g), 40113, 44701. of this AD, at the applicable time specified
for practices, methods, and procedures in paragraph 1.E., ‘‘Compliance,’’ of Boeing
the Administrator finds necessary for § 39.13 [Amended] Alert Service Bulletin 747–53A2463,
safety in air commerce. This regulation Revision 2, dated June 16, 2014, do an
is within the scope of that authority ■ 2. The FAA amends § 39.13 by external low frequency eddy current
because it addresses an unsafe condition removing Airworthiness Directive (AD) inspection for corrosion at the upper row of
that is likely to exist or develop on 2004–13–02, Amendment 39–13682 (69 fasteners in the lap joint, and do all
products identified in this rulemaking FR 35237, June 24, 2004), and adding applicable corrective actions, in accordance
the following new AD: with the Accomplishment Instructions of
action.
Boeing Alert Service Bulletin 747–53A2463,
Regulatory Findings 2015–15–01 The Boeing Company: Revision 2, dated June 16, 2014, except as
Amendment 39–18210; Docket No. provided by paragraph (l)(1) of this AD. Do
We have determined that this AD will FAA–2014–1052; Directorate Identifier all applicable corrective actions before
not have federalism implications under 2014–NM–140–AD. further flight. Repeat the inspection at the
Executive Order 13132. This AD will upper row of fasteners in the lap joint
(a) Effective Date
not have a substantial direct effect on thereafter at the applicable intervals specified
the States, on the relationship between This AD is effective August 28, 2015. in paragraph 1.E., ‘‘Compliance,’’ of Boeing
the national government and the States, Alert Service Bulletin 747–53A2463,
(b) Affected ADs
Revision 2, dated June 16, 2014, except as
or on the distribution of power and This AD replaces AD 2004–13–02, provided by paragraph (l)(3) of this AD.
responsibilities among the various Amendment 39–13682 (69 FR 35237, June Accomplishment of a structural modification
levels of government. 24, 2004). in accordance with Part 5 of Boeing Alert
For the reasons discussed above, I Service Bulletin 747–53A2463, Revision 2,
(c) Applicability
certify that this AD: dated June 16, 2014, except as provided by
(1) Is not a ‘‘significant regulatory This AD applies to The Boeing Company paragraph (l)(1) of this AD, terminates the
action’’ under Executive Order 12866, Model 747–100, –200B, and –200F series inspection requirements of this paragraph in
airplanes, certificated in any category, as the area of the modification only. The actions
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(2) Is not a ‘‘significant rule’’ under
identified in Boeing Alert Service Bulletin required by paragraph (j) of this AD are still
DOT Regulatory Policies and Procedures
747–53A2463, Revision 2, dated June 16, applicable in the area of the modification.
(44 FR 11034, February 26, 1979), 2014.
(3) Will not affect intrastate aviation (h) Inspections for Cracking, and Corrective
in Alaska, and (d) Subject Actions
(4) Will not have a significant Air Transport Association (ATA) of For airplanes identified as Groups 2
economic impact, positive or negative, America Code 53, Fuselage. through 14 in Boeing Alert Service Bulletin
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![43944 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations
(IBR) of the service information listed in this regulations to be abandoned under the work spaces authorized for the
paragraph under 5 U.S.C. 552(a) and 1 CFR blanket certificate regulations, subject to construction and operation of interstate
part 51. those regulations’ requirements. transmission facilities.
(2) You must use this service information 2. On December 22, 2014, National
as applicable to do the actions required by DATES: This rule will become effective
October 7, 2015. Fuel Gas Supply Corporation and
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 747– FOR FURTHER INFORMATION CONTACT:
Empire Pipeline, Inc. (collectively,
53A2463, Revision 2, dated June 16, 2014. National Fuel) filed a request that the
Katherine Liberty, Office of the General Commission revise its part 157, subpart
(ii) Reserved. Counsel, Federal Energy Regulatory
(3) For Boeing service information F, blanket certificate regulations to
Commission, 888 First Street NE., provide a mechanism under those
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data & Washington, DC 20426, (202) 502– regulations for the abandonment of
Services Management, P.O. Box 3707, MC 6491, katherine.liberty@ferc.gov. auxiliary facilities that were constructed
2H–65, Seattle, WA 98124–2207; telephone Gordon Wagner, Office of the General under section 2.55(a) and replacement
206–544–5000, extension 1; fax 206–766– Counsel, Federal Energy Regulatory facilities that were constructed under
5680; Internet https:// Commission, 888 First Street NE., section 2.55(b). National Fuel also
www.myboeingfleet.com. Washington, DC 20426, (202) 502–
(4) You may view this service information
requests clarification that in addition to
8947, gordon.wagner@ferc.gov. authorizing new auxiliary installations,
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For Howard Wheeler, Office of Energy section 2.55(a) also authorizes the
information on the availability of this Projects, Federal Energy Regulatory replacement of existing auxiliary
material at the FAA, call 425–227–1221. Commission, 888 First Street NE., facilities without the need for
(5) You may view this service information Washington, DC 20426, (202) 502– abandonment authority under section
that is incorporated by reference at the 8688, howard.wheeler@ferc.gov. 7(b) of the Natural Gas Act (NGA).
National Archives and Records Shannon Jones, Office of Energy 3. As discussed below, this order
Administration (NARA). For information on responds to National Fuel’s requests by
Projects, Federal Energy Regulatory
the availability of this material at NARA, call (1) adopting a new subsection 2.55(a)(3)
202–741–6030, or go to: http:// Commission, 888 First Street NE.,
Washington, DC 20426, (202) 502– to provide pre-granted authority to
www.archives.gov/federal-register/cfr/ibr-
locations.html. 6410, shannon.jones@ferc.gov. abandon or replace auxiliary facilities,
subject to certain conditions; (2)
Issued in Renton, Washington, on July 10, SUPPLEMENTARY INFORMATION:
amending part 157 to provide authority,
2015. ORDER NO. 790–B subject to the blanket certificate
Michael Kaszycki, regulations’ conditions, to abandon
Table of Contents
Acting Manager, Transport Airplane section 2.55(a) auxiliary facilities that
Directorate, Aircraft Certification Service. cannot meet the conditions for the pre-
Paragraph
[FR Doc. 2015–17978 Filed 7–23–15; 8:45 am] Nos. granted abandonment authority being
BILLING CODE 4910–13–P added to section 2.55(a) and to abandon
I. Discussion ............................. 4 section 2.55(b) replacement facilities.
A. Section 2.55(a) Auxil-
iary Facilities ................ 9 I. Discussion
DEPARTMENT OF ENERGY B. Section 2.55(b) Re- 4. In Order No. 790–A, the
placements .................... 14 Commission explained that section 2.55
Federal Energy Regulatory II. Information Collection
Commission Statement .............................. 18
facilities are installed under the
III. Environmental Analysis .... 23 certificate authority that authorized the
18 CFR Parts 2 and 157 IV. Regulatory Flexibility Act 24 interstate transmission pipeline
V. Document Availability ....... 26 facilities being augmented or replaced.
[Docket No. RM12–11–003; Order No. 790– VI. Effective Date and Con- The Commission further explained that
B] gressional Notification ......... 29 because section 2.55 auxiliary and
Revisions to Auxiliary Installations, Order No. 790–B replacement facilities are certificated
Replacement Facilities, and Siting and facilities, a company needs prior
Final Rule authorization under NGA section 7(b) to
Maintenance Regulations
Order on Rehearing and Clarification abandon such facilities. The
AGENCY: Federal Energy Regulatory Commission stated that in many
Commission. 1. On November 20, 2014, the Federal instances companies should be able to
Energy Regulatory Commission rely on their part 157, subpart F, blanket
ACTION: Final rule, order on
(Commission) issued Order No. 790–A,1 certificate authority to abandon section
clarification. which affirmed, inter alia, the 2.55 facilities. In view of this statement,
SUMMARY: The Federal Energy Commission’s clarification in Order No. National Fuel believes it is the
Regulatory Commission (Commission) is 790 2 that auxiliary facilities installed Commission’s intent that companies be
amending its regulations to: Provide under section 2.55(a) of the able to rely on their part 157 blanket
pre-granted authority under a new Commission’s regulations 3 may only certificate authority to abandon facilities
paragraph to abandon or replace utilize rights-of-way, facility sites, and installed under section 2.55.
auxiliary facilities, subject to certain 1 Revisions to Auxiliary Installations,
5. National Fuel points out, however,
conditions; permit auxiliary facilities Replacement Facilities, and Siting and
that section 157.202(b)(3) of the blanket
that cannot meet the conditions for the certificate regulations states that a
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Maintenance Regulations, Order No. 790–A, 79 FR
pre-granted abandonment authority in 70056 (Nov. 25, 2014), FERC Stats. & Regs. ¶ 31,361 ‘‘facility’’ for purposes of the blanket
the new paragraph to be abandoned (2014) (cross-referenced at 149 FERC ¶ 61,144 program does not include a facility
(2014)).
under the blanket certificate regulations, 2 Order No. 790, 78 FR 72794–801 (Dec. 4, 2013),
‘‘described under section 2.55,’’ and that
subject to those regulations’ FERC Stats. & Regs. ¶ 31,351 (2013) (cross- section 157.216 states that blanket
requirements; and permit replacement referenced at 145 FERC ¶ 61,154 (2013)). certificate abandonment authority is
facilities constructed under the 3 18 CFR 2.55 (2014). limited to facilities that ‘‘did or could
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Document Created: 2018-02-23 09:24:35
Document Modified: 2018-02-23 09:24:35
| 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 August 28, 2015. | |
| Contact | Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 43940 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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