80 FR 74052 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 228 (November 27, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 228 (November 27, 2015)
| Page Range | 74052-74056 | |
| FR Document | 2015-30120 |
[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)] [Proposed Rules] [Pages 74052-74056] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-30120] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-5816; Directorate Identifier 2015-NM-029-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2006-10- 16, which applies to all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2006-10-16 requires, for certain airplanes, repetitive inspections for cracking of the outboard and center sections of the horizontal stabilizer, and repair if necessary. For certain other airplanes, AD 2006-10-16 requires a detailed inspection to determine the type of fasteners, and related investigative actions and repair if necessary. Since we issued AD 2006- 10-16, additional cracking was found in the splice plates, hinge fittings, terminal fittings, the upper skin of the outboard and center sections, and the rear spar webs before reaching the inspection interval specified in AD 2006-10-16. Cracked and fractured Maraging steel fasteners were also found. This proposed AD would reduce the compliance time for certain inspections and would add repetitive inspections for cracking of the splice plates, hinge fittings, terminal fittings, the upper skin of the outboard and center sections, and the rear spar webs in Zone B. This proposed AD would also add an inspection to determine whether fasteners are magnetic in Zone C, repetitive ultrasonic inspections for cracking and fractures of affected fasteners, and related investigative and corrective actions if necessary. This proposed AD would also add an optional modification, which would terminate certain repetitive inspections, and would add post-modification inspections and corrective action if necessary. We are proposing this AD to detect and correct this cracking, which could lead to reduced structural capability of the outboard and center sections of the horizontal stabilizer and could result in loss of control of the airplane. DATES: We must receive comments on this proposed AD by January 11, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 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-2015-5816. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 5816; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: nathan.p.weigand@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about [[Page 74053]] this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-5816; Directorate Identifier 2015-NM-029-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On May 8, 2006, we issued AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006), for all The Boeing Company Model 747-100, 747- 100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2006-10-16 requires, for certain airplanes, repetitive inspections for cracking of the outboard and center sections of the horizontal stabilizer, and repair if necessary. For certain other airplanes, AD 2006-10-16 requires a detailed inspection to determine the type of fasteners, related investigative actions, and repair if necessary. AD 2006-10-16 resulted from reports of cracking in the outboard and center section of the aft upper skin of the horizontal stabilizer, the rear spar chord, rear spar web, terminal fittings, and splice plates; and a report of fractured and cracked steel fasteners. We issued AD 2006-10-16 to detect and correct this cracking, which could lead to reduced structural capability of the outboard and center sections of the horizontal stabilizer and could result in loss of control of the airplane. Actions Since AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006), Was Issued Since we issued AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006), additional cracking was found in the splice plates, hinge fittings, terminal fittings, the upper skin of the outboard and center sections, and the rear spar webs before reaching the inspection interval specified in AD 2006-10-16. Cracked and fractured Maraging steel fasteners were also found. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015. The service information describes procedures for accomplishing Zone A, Zone B, and Zone C inspections for cracking of the upper skin and upper rear spar chord of the outboard and center sections of the horizontal stabilizer, and related investigative and corrective actions if necessary. The service information also describes procedures for a magnetic inspection to determine the type of fasteners, ultrasonic inspections for cracking and fractures of affected fasteners, and related investigative actions and corrective actions if necessary. The service information also describes procedures for an optional modification, which would end certain repetitive inspections, and procedures for post-modification inspections and corrective action if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements Although this proposed AD does not explicitly restate the requirements of AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006), this proposed AD would retain all of the requirements. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraph (g) of this proposed AD. This proposed AD would reduce the compliance time for certain inspections and add new repetitive inspections for cracking of the splice plates, hinge fittings, terminal fittings, the upper skin of the outboard and center sections, and the rear spar webs in Zone B. This proposed AD would also add an inspection to determine whether fasteners are magnetic in Zone C (made of H-11 steel), repetitive ultrasonic inspections for cracking and fractures of affected fasteners, and related investigative and corrective actions if necessary. This proposed AD would also add an optional modification, which would end certain repetitive inspections, and procedures for post-modification inspections and corrective action if necessary. This proposed AD also adds optional open-hole NDT inspections (high frequency eddy current inspections) for certain airplanes, for Zone B inspections. This proposed AD would also require accomplishing the actions specified in the service information described previously, except as discussed under ``Difference Between this Proposed AD and the Service Bulletin.'' For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-5816. The phrase ``related investigative actions'' is used in this proposed AD. ``Related investigative actions'' are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. ``Corrective actions'' are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Difference Between This Proposed AD and the Service Bulletin Although Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, specifies that operators may contact the manufacturer for disposition of certain repair conditions, this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 116 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: [[Page 74054]] Estimated Costs--Required Actions ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Zone A Inspections (required by AD 8 work-hours x $85 $0 $680 Up to $78,880. 2006-10-16, Amendment 39-14600). per hour = $680. Zone B Open-hole NDT Inspection 30 work-hours x 85 0 2,550 Up to $295,800. (required by AD 2006-10-16, per hour = 2,550. Amendment 39-14600 for Groups 3, 4, and 5 airplanes; and for Groups 1, 2, and 3 airplanes, if done). Zone C Maraging or H-11 Steel 8 work-hours x 85 per 0 680 Up to $78,880. Fastener Inspection (required by hour = 680. AD 2006-10-16, Amendment 39-14600 for Groups 1, 2, and 3 airplanes). New Zone B proposed inspections... 248 work-hours x 85 0 21,080 $2,445,280. per hour = 21,080. New Zone C proposed inspection.... 26 work-hours x 85 0 2,210 $256,360. per hour = 2,210. ---------------------------------------------------------------------------------------------------------------- Estimated Costs--Optional Actions ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Open-hole NDT inspections (high Up to 298 work-hours x $$0.................... Up to $25,330. frequency eddy current inspections. $85 per hour = up to $25,330. Zone B Modification.................. Up to 313 work-hours x Up to $3,486........... Up to $30,091. $85 per hour = up to $26,605. Post-Modification Inspections........ Up to 298 work-hours x $0..................... Up to $25,330. $85 per hour = up to $25,330. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006), and adding the following new AD: The Boeing Company: Docket No. FAA-2015-5816; Directorate Identifier 2015-NM-029-AD. (a) Comments Due Date The FAA must receive comments on this AD action by January 11, 2016. (b) Affected ADs This AD replaces AD 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006). (c) Applicability This AD applies to all The Boeing Company Model 747-100, 747- 100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by reports of cracking found in the splice plates, hinge fittings, terminal fittings, the upper skin of the outboard and center sections, and the rear spar webs before reaching the inspection interval specified in AD 2006-10-16. Cracked and fractured Maraging steel fasteners were also found. We are issuing this AD to detect and correct this cracking, which [[Page 74055]] could lead to reduced structural capability of the outboard and center sections of the horizontal stabilizer and could result in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections/Investigative and Corrective Actions At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, except as required by paragraphs (h)(1) and (h)(2) of this AD: Do the applicable actions specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, and all applicable related investigative and corrective actions, in accordance with the applicable part of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, except as required by paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747- 55A2050, Revision 2, dated January 23, 2015. (1) For Group 1 through 3 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do non- destructive test (NDT) inspections (ultrasonic, high frequency eddy current, and low frequency eddy current inspections) or open-hole NDT inspections (high frequency eddy current inspections), of Zone B for cracking in accordance with Part 3 or Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, as applicable. (2) For Group 4 through 6 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do open- hole NDT inspections (high frequency eddy current inspections), of Zone B for cracking in accordance with Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015. (3) For Group 7 through 9 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do inspections of Zone A (detailed or high frequency eddy current inspections) and Zone B (high frequency eddy current inspections) for cracking, in accordance with Part 1, Part 2, or Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, as applicable. (4) For Group 1 through 3 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do an inspection of Zone C Maraging or H-11 steel fasteners to determine whether fasteners are magnetic, in accordance with Part 6 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015. (h) Exceptions to Service Bulletin Specifications (1) Where Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, 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. (2) The Condition column of Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, refers to ``airplanes with certain total flight cycles and total flight hours.'' This AD, however, applies to the airplanes with the specified total flight cycles and total flight hours as of the effective date of this AD. (3) Where Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (i) Optional Terminating Action (1) For Group 1 through 3 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Accomplishing the Zone B modification, including all applicable related investigative and corrective actions, specified in Part 7 of the Accomplishment Instructions of Boeing Service Bulletin 747- 55A2050, Revision 2, dated January 23, 2015, except as required by paragraph (h)(3) of this AD, terminates the repetitive inspections specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD for the modified area only. (i) Inspections required by paragraph (g)(1) of this AD for Zone B, as specified in Part 3 and Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015. (ii) Inspections required by paragraph (g)(4) of this AD for Zone C, as specified in Part 5 and Part 6 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015. (2) For Group 1 through 3 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Accomplishing the Zone B open hole NDT inspection, repairing any cracking as applicable, and replacing fasteners as specified in Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747- 55A2050, Revision 2, dated January 23, 2015, terminates the repetitive ultrasonic inspections required by paragraph (g)(4) of this AD for Zone C, as specified in Part 6 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, for the inspected area only. (3) For Group 4 through 9 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Accomplishing the Zone B modification, including all applicable related investigative and corrective actions, specified in Part 7 of the Accomplishment Instructions of Boeing Service Bulletin 747- 55A2050, Revision 2, dated January 23, 2015, except as required by paragraph (h)(3) of this AD, terminates the repetitive inspections required by paragraph (g)(2) or (g)(3) of this AD, as applicable, only for Zone B, as specified in Part 4 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, for the modified area only. (j) Repetitive Post-Modification Inspections and Corrective Actions At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015: Do the applicable inspections specified in paragraphs (j)(1) and (j)(2) of this AD and all applicable corrective actions, in accordance with Part 8 of the Accomplishment Instructions of Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, except as required by paragraph (h)(3) of this AD. Do all applicable corrective actions before further flight. Repeat the applicable inspections at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747- 55A2050, Revision 2, dated January 23, 2015. (1) For Group 1 through 3 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015 on which the Zone B modification specified in paragraph (i)(1) of this AD is done: Do non-destructive test (NDT) inspections (ultrasonic, high frequency eddy current, and low frequency eddy current inspections) or open-hole NDT inspections (high frequency eddy current inspections) of Zone B for cracking. (2) For Group 4 through 9 airplanes identified in Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015 on which the Zone B modification specified in paragraph (i)(3) of this AD is done: Do open-hole NDT inspections (high frequency eddy current inspections) of Zone B for cracking. (k) Parts Installation Prohibition As of the effective date of this AD, no person may install any Maraging or H-11 steel fasteners in the locations specified in this AD. Where Boeing Service Bulletin 747-55A2050, Revision 2, dated January 23, 2015, specifies to install H-11 bolts (kept fasteners), this AD requires installation of Inconel bolts. (l) 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 (m)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-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. [[Page 74056]] (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 2006-10-16, Amendment 39-14600 (71 FR 28570, May 17, 2006), are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD, except for approved AMOCs that allow installation of Maraging or H-11 steel fasteners. (m) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: nathan.p.weigand@faa.gov. (2) 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. Issued in Renton, Washington, on November 19, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-30120 Filed 11-25-15; 8:45 am] BILLING CODE 4910-13-P
![74052 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
(u) Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION DATES: We must receive comments on
(AMOCs) this proposed AD by January 11, 2016.
(1) The Manager, Los Angeles Aircraft Federal Aviation Administration ADDRESSES: You may send comments,
Certification Office (ACO), FAA, has the using the procedures found in 14 CFR
authority to approve AMOCs for this AD, if 14 CFR Part 39 11.43 and 11.45, by any of the following
requested using the procedures found in 14 [Docket No. FAA–2015–5816; Directorate methods:
CFR 39.19. In accordance with 14 CFR 39.19, Identifier 2015–NM–029–AD] • Federal eRulemaking Portal: Go to
send your request to your principal inspector http://www.regulations.gov. Follow the
or local Flight Standards District Office, as RIN 2120–AA64 instructions for submitting comments.
appropriate. If sending information directly • Fax: 202–493–2251.
to the manager of the ACO, send it to the Airworthiness Directives; The Boeing • Mail: U.S. Department of
attention of the person identified in Company Airplanes Transportation, Docket Operations, M–
paragraph (v)(1) of this AD. Information may AGENCY: Federal Aviation 30, West Building Ground Floor, Room
be emailed to: 9-ANM-LAACO-AMOC- Administration (FAA), DOT. W12–140, 1200 New Jersey Avenue SE.,
Requests@faa.gov. Washington, DC 20590.
ACTION: Notice of proposed rulemaking
(2) Before using any approved AMOC,
(NPRM). • Hand Delivery: Deliver to Mail
notify your appropriate principal inspector, address above between 9 a.m. and 5
or lacking a principal inspector, the manager SUMMARY: We propose to supersede p.m., Monday through Friday, except
of the local flight standards district office/ Airworthiness Directive (AD) 2006–10– Federal holidays.
certificate holding district office. For service information identified in
16, which applies to all The Boeing
(3) An AMOC that provides an acceptable this proposed AD, contact Boeing
Company Model 747–100, 747–100B,
level of safety may be used for any repair, Commercial Airplanes, Attention: Data
747–100B SUD, 747–200B, 747–200C,
modification, or alteration required by this & Services Management, P. O. Box 3707,
747–200F, 747–300, 747–400, 747–
AD if it is approved by the Boeing MC 2H–65, Seattle, WA 98124–2207;
400D, 747–400F, 747SR, and 747SP
Commercial Airplanes Organization telephone: 206–544–5000, extension 1;
series airplanes. AD 2006–10–16
Designation Authorization (ODA) that has
requires, for certain airplanes, repetitive fax: 206–766–5680; Internet https://
been authorized by the Manager, Seattle
inspections for cracking of the outboard www.myboeingfleet.com. You may view
ACO, to make those findings. To be
and center sections of the horizontal this referenced service information at
approved, the repair method, modification
stabilizer, and repair if necessary. For the FAA, Transport Airplane
deviation, or alteration deviation must meet
certain other airplanes, AD 2006–10–16 Directorate, 1601 Lind Avenue SW.,
the certification basis of the airplane and the
requires a detailed inspection to Renton, WA. For information on the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2009–02–06, determine the type of fasteners, and availability of this material at the FAA,
Amendment 39–15796 (74 FR 10469, March related investigative actions and repair call 425–227–1221. It is also available
11, 2009); AD 2009–02–06 R1, Amendment if necessary. Since we issued AD 2006– on the Internet at http://
39–16015 (74 FR 45979, September 6, 2009); 10–16, additional cracking was found in www.regulations.gov by searching for
and AD 2011–23–05, Amendment 39–16856 the splice plates, hinge fittings, terminal and locating Docket No. FAA–2015–
(76 FR 67343, November 1, 2011); are fittings, the upper skin of the outboard 5816.
approved as AMOCs for the corresponding and center sections, and the rear spar Examining the AD Docket
provisions of this AD. webs before reaching the inspection
interval specified in AD 2006–10–16. You may examine the AD docket on
(v) Related Information Cracked and fractured Maraging steel the Internet at http://
(1) For more information about this AD, fasteners were also found. This www.regulations.gov by searching for
contact Wayne Lockett, Aerospace Engineer, proposed AD would reduce the and locating Docket No. FAA–2015–
Airframe Branch, ANM–120S, Seattle compliance time for certain inspections 5816; or in person at the Docket
Aircraft Certification Office (ACO), FAA, and would add repetitive inspections Management Facility between 9 a.m.
1601 Lind Avenue SW., Renton, Washington for cracking of the splice plates, hinge and 5 p.m., Monday through Friday,
98057–3356; phone: 425–917–6447; fax: 425– fittings, terminal fittings, the upper skin except Federal holidays. The AD docket
917–6590; email: wayne.lockett@faa.gov. of the outboard and center sections, and contains this proposed AD, the
(2) For service information identified in the rear spar webs in Zone B. This regulatory evaluation, any comments
this AD, contact Boeing Commercial proposed AD would also add an received, and other information. The
Airplanes, Attention: Data & Services inspection to determine whether street address for the Docket Office
Management, P. O. Box 3707, MC 2H–65, fasteners are magnetic in Zone C, (phone: 800–647–5527) is in the
Seattle, WA 98124–2207; telephone 206– repetitive ultrasonic inspections for ADDRESSES section. Comments will be
544–5000, extension 1; fax 206–766–5680; cracking and fractures of affected available in the AD docket shortly after
Internet https://www.myboeingfleet.com. You fasteners, and related investigative and receipt.
may view this referenced service information corrective actions if necessary. This FOR FURTHER INFORMATION CONTACT:
at the FAA, 1601 Lind Avenue SW., Renton, proposed AD would also add an Nathan Weigand, Aerospace Engineer,
Washington. For information on the optional modification, which would Airframe Branch, ANM–120S, FAA,
availability of this material at the FAA, call terminate certain repetitive inspections, Seattle Aircraft Certification Office,
425–227–1221. 1601 Lind Avenue SW., Renton, WA
and would add post-modification
mstockstill on DSK4VPTVN1PROD with PROPOSALS
Issued in Renton, Washington, on inspections and corrective action if 98057–3356; phone: 425–917–6428; fax:
November 17, 2015. necessary. We are proposing this AD to 425–917–6590; email:
Jeffrey E. Duven, detect and correct this cracking, which nathan.p.weigand@faa.gov.
Manager, Transport Airplane Directorate, could lead to reduced structural SUPPLEMENTARY INFORMATION:
Aircraft Certification Service. capability of the outboard and center
sections of the horizontal stabilizer and Comments Invited
[FR Doc. 2015–30008 Filed 11–25–15; 8:45 am]
could result in loss of control of the We invite you to send any written
BILLING CODE 4910–13–P
airplane. relevant data, views, or arguments about
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![74054 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
ESTIMATED COSTS—REQUIRED ACTIONS
Cost per
Action Labor cost Parts cost Cost on U.S. operators
product
Zone A Inspections (required by AD 2006– 8 work-hours × $85 per hour $0 $680 Up to $78,880.
10–16, Amendment 39–14600). = $680.
Zone B Open-hole NDT Inspection (required 30 work-hours × 85 per hour 0 2,550 Up to $295,800.
by AD 2006–10–16, Amendment 39–14600 = 2,550.
for Groups 3, 4, and 5 airplanes; and for
Groups 1, 2, and 3 airplanes, if done).
Zone C Maraging or H–11 Steel Fastener In- 8 work-hours × 85 per hour = 0 680 Up to $78,880.
spection (required by AD 2006–10–16, 680.
Amendment 39–14600 for Groups 1, 2,
and 3 airplanes).
New Zone B proposed inspections ................ 248 work-hours × 85 per hour 0 21,080 $2,445,280.
= 21,080.
New Zone C proposed inspection .................. 26 work-hours × 85 per hour 0 2,210 $256,360.
= 2,210.
ESTIMATED COSTS—OPTIONAL ACTIONS
Action Labor cost Parts cost Cost per product
Open-hole NDT inspections (high Up to 298 work-hours × $85 per $$0 ................................................ Up to $25,330.
frequency eddy current inspec- hour = up to $25,330.
tions.
Zone B Modification ....................... Up to 313 work-hours × $85 per Up to $3,486 ................................. Up to $30,091.
hour = up to $26,605.
Post-Modification Inspections ........ Up to 298 work-hours × $85 per $0 .................................................. Up to $25,330.
hour = up to $25,330.
We have received no definitive data national Government and the States, or § 39.13 [Amended]
that would enable us to provide a cost on the distribution of power and ■ 2. The FAA amends § 39.13 by
estimate for the on-condition actions responsibilities among the various removing Airworthiness Directive AD
specified in this proposed AD. levels of government. 2006–10–16, Amendment 39–14600 (71
For the reasons discussed above, I FR 28570, May 17, 2006), and adding
Authority for This Rulemaking
certify that the proposed regulation: the following new AD:
Title 49 of the United States Code (1) Is not a ‘‘significant regulatory The Boeing Company: Docket No. FAA–
specifies the FAA’s authority to issue action’’ under Executive Order 12866, 2015–5816; Directorate Identifier 2015–
rules on aviation safety. Subtitle I, (2) Is not a ‘‘significant rule’’ under NM–029–AD.
Section 106, describes the authority of the DOT Regulatory Policies and (a) Comments Due Date
the FAA Administrator. Subtitle VII, Procedures (44 FR 11034, February 26,
Aviation Programs, describes in more The FAA must receive comments on this
1979), AD action by January 11, 2016.
detail the scope of the Agency’s (3) Will not affect intrastate aviation
authority. in Alaska, and (b) Affected ADs
We are issuing this rulemaking under (4) Will not have a significant This AD replaces AD 2006–10–16,
the authority described in Subtitle VII, economic impact, positive or negative, Amendment 39–14600 (71 FR 28570, May 17,
Part A, Subpart III, Section 44701, on a substantial number of small entities 2006).
‘‘General requirements.’’ Under that under the criteria of the Regulatory (c) Applicability
section, Congress charges the FAA with Flexibility Act. This AD applies to all The Boeing
promoting safe flight of civil aircraft in Company Model 747–100, 747–100B, 747–
air commerce by prescribing regulations List of Subjects in 14 CFR Part 39
100B SUD, 747–200B, 747–200C, 747–200F,
for practices, methods, and procedures Air transportation, Aircraft, Aviation 747–300, 747–400, 747–400D, 747–400F,
the Administrator finds necessary for safety, Incorporation by reference, 747SR, and 747SP series airplanes;
safety in air commerce. This regulation Safety. certificated in any category.
is within the scope of that authority (d) Subject
because it addresses an unsafe condition The Proposed Amendment
Air Transport Association (ATA) of
that is likely to exist or develop on Accordingly, under the authority America Code 55, Stabilizers.
products identified in this rulemaking delegated to me by the Administrator,
action. the FAA proposes to amend 14 CFR part (e) Unsafe Condition
mstockstill on DSK4VPTVN1PROD with PROPOSALS
39 as follows: This AD was prompted by reports of
Regulatory Findings cracking found in the splice plates, hinge
We have determined that this PART 39—AIRWORTHINESS fittings, terminal fittings, the upper skin of
DIRECTIVES the outboard and center sections, and the rear
proposed AD would not have federalism spar webs before reaching the inspection
implications under Executive Order interval specified in AD 2006–10–16.
13132. This proposed AD would not ■ 1. The authority citation for part 39
Cracked and fractured Maraging steel
have a substantial direct effect on the continues to read as follows: fasteners were also found. We are issuing this
States, on the relationship between the Authority: 49 U.S.C. 106(g), 40113, 44701. AD to detect and correct this cracking, which
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![74056 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
(3) An AMOC that provides an acceptable boxes and restoring the sealing. We are Comments Invited
level of safety may be used for any repair proposing this AD to detect and correct
required by this AD if it is approved by the We invite you to send any written
failure of a connector or coupling on a relevant data, views, or arguments about
Boeing Commercial Airplanes Organization fuel line, which, in combination with a
Designation Authorization (ODA) that has this proposed AD. Send your comments
been authorized by the Manager, Seattle
leak in the corresponding enclosure to an address listed under the
ACO, to make those findings. For a repair (i.e., fuel box), could result in a fire in ADDRESSES section. Include ‘‘Docket No.
method to be approved, the repair must meet the baggage compartment and affect the FAA–2015–5813; Directorate Identifier
the certification basis of the airplane, and the safe flight of the airplane. 2014–NM–111–AD’’ at the beginning of
approval must specifically refer to this AD. DATES: We must receive comments on your comments. We specifically invite
(4) AMOCs approved for AD 2006–10–16, this proposed AD by January 11, 2016. comments on the overall regulatory,
Amendment 39–14600 (71 FR 28570, May 17,
ADDRESSES: You may send comments, economic, environmental, and energy
2006), are approved as AMOCs for the
corresponding provisions of paragraph (g) of using the procedures found in 14 CFR aspects of this proposed AD. We will
this AD, except for approved AMOCs that 11.43 and 11.45, by any of the following consider all comments received by the
allow installation of Maraging or H–11 steel methods: closing date and may amend this
fasteners. • Federal eRulemaking Portal: Go to proposed AD based on those comments.
http://www.regulations.gov. Follow the We will post all comments we
(m) Related Information
instructions for submitting comments. receive, without change, to http://
(1) For more information about this AD, • Fax: 202–493–2251. www.regulations.gov, including any
contact Nathan Weigand, Aerospace • Mail: U.S. Department of
Engineer, Airframe Branch, ANM–120S,
personal information you provide. We
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Transportation, Docket Operations, M– will also post a report summarizing each
Renton, WA 98057–3356; phone: 425–917– 30, West Building Ground Floor, Room substantive verbal contact we receive
6428; fax: 425–917–6590; email: W12–140, 1200 New Jersey Avenue SE., about this proposed AD.
nathan.p.weigand@faa.gov. Washington, DC 20590.
(2) For service information identified in • Hand Delivery: U.S. Department of Discussion
this AD, contact Boeing Commercial Transportation, Docket Operations, M– The European Aviation Safety Agency
Airplanes, Attention: Data & Services 30, West Building Ground Floor, Room (EASA), which is the Technical Agent
Management, P. O. Box 3707, MC 2H–65, W12–140, 1200 New Jersey Avenue SE., for the Member States of the European
Seattle, WA 98124–2207; telephone: 206– Washington, DC, between 9 a.m. and 5 Union, has issued EASA Airworthiness
544–5000, extension 1; fax: 206–766–5680;
p.m., Monday through Friday, except Directive 2014–0116, dated May 13,
Internet https://www.myboeingfleet.com. You
may view this referenced service information Federal holidays. 2014 (referred to after this as the
at the FAA, Transport Airplane Directorate, For service information identified in Mandatory Continuing Airworthiness
1601 Lind Avenue SW., Renton, WA. For this proposed AD, contact Dassault Information, or ‘‘the MCAI’’), to correct
information on the availability of this Falcon Jet, P.O. Box 2000, South an unsafe condition for certain Dassault
material at the FAA, call 425–227–1221. Hackensack, NJ 07606; telephone 201– Aviation Model FALCON 7X airplanes.
Issued in Renton, Washington, on 440–6700; Internet http:// The MCAI states:
November 19, 2015. www.dassaultfalcon.com. You may During the fuel system pressurization of a
Michael Kaszycki, view this referenced service information production line Falcon 7X aeroplane, a fuel
at the FAA, Transport Airplane leak occurred in the baggage compartment.
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service. Directorate, 1601 Lind Avenue SW., The technical investigations concluded that a
Renton, WA. For information on the double failure of a connector (or coupling) on
[FR Doc. 2015–30120 Filed 11–25–15; 8:45 am]
availability of this material at the FAA, a fuel line, in combination with a defective
BILLING CODE 4910–13–P fuel tightness of the corresponding enclosure
call 425–227–1221.
(fuel box), caused the leak.
Examining the AD Docket Failure of the second barrier (fuel box) is
DEPARTMENT OF TRANSPORTATION a dormant failure, as this will only manifest
You may examine the AD docket on
itself in case of connector (or fuel pipe
Federal Aviation Administration the Internet at http:// coupling) failure in flight.
www.regulations.gov by searching for This condition, if not corrected, could
14 CFR Part 39 and locating Docket No. FAA–2015– result in a fire in the baggage compartment,
5813; or in person at the Docket which would affect the aeroplane safe flight.
[Docket No. FAA–2015–5813; Directorate Management Facility between 9 a.m. To address this potential unsafe condition,
Identifier 2014–NM–111–AD] and 5 p.m., Monday through Friday, Dassault Aviation issued Service Bulletin
RIN 2120–AA64 except Federal holidays. The AD docket (SB) F7X–284, which provides instructions to
contains this proposed AD, the restore the sealing of the Left Hand (LH) and
Airworthiness Directives; Dassault regulatory evaluation, any comments Right Hand (RH) fuel boxes.
Aviation Airplanes For the reasons described above, this
received, and other information. The [EASA] AD requires opening of the fuel
street address for the Docket Operations boxes and restoration of the sealing of the
AGENCY: Federal Aviation
office (telephone 800–647–5527) is in fuel boxes to meet the initial design
Administration (FAA), DOT.
the ADDRESSES section. Comments will specifications.
ACTION: Notice of proposed rulemaking
be available in the AD docket shortly
(NPRM). You may examine the MCAI in the
after receipt.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
AD docket on the Internet at http://
SUMMARY: We propose to adopt a new FOR FURTHER INFORMATION CONTACT: Tom www.regulations.gov by searching for
airworthiness directive (AD) for certain Rodriguez, Aerospace Engineer, and locating Docket No. FAA–2015–
Dassault Aviation Model FALCON 7X International Branch, ANM–116, 5813.
airplanes. This proposed AD was Transport Airplane Directorate, FAA,
prompted by a fuel leak that occurred in 1601 Lind Avenue SW., Renton, WA Related Service Information Under 1
the baggage compartment during fuel 98057–3356; telephone (425) 227–1137; CFR Part 51
system pressurization. This proposed fax (425) 227–1149. Dassault Aviation has issued Service
AD would require opening the fuel SUPPLEMENTARY INFORMATION: Bulletin 7X–284, Revision 1, dated
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Document Created: 2015-12-14 14:05:56
Document Modified: 2015-12-14 14:05:56
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by January 11, 2016. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 74052 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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