80 FR 60303 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 193 (October 6, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 193 (October 6, 2015)
| Page Range | 60303-60307 | |
| FR Document | 2015-25272 |
[Federal Register Volume 80, Number 193 (Tuesday, October 6, 2015)] [Proposed Rules] [Pages 60303-60307] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-25272] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3983; Directorate Identifier 2015-NM-141-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 adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-300, 747SR, and 747SP series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper chords of the upper deck floor beams are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive inspections for cracks at the floor panel attachment fastener holes; repetitive inspections for cracks in the upper and lower chords of the upper deck floor beams at permanent fastener locations; repetitive inspections for cracks in certain repaired and modified areas; and related investigative and corrective actions if necessary. This proposed AD would also require repetitive replacement of the upper chords of the upper deck floor beams, including pre- replacement inspections and corrective action if necessary; and post- replacement repetitive inspections and repair if necessary. We are proposing this AD to detect and correct fatigue cracking of the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by November 20, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 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- 3983. 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- 3983; 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 [[Page 60304]] (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Roger Caldwell, Aerospace Engineer, Technical Operations Center, ANM-100D, FAA, Denver Aircraft Certification Office, 26805 East 68th Avenue, Room 214, Denver, CO 80249; phone: 303-342-1086; fax: 303-342-1088; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-3983; Directorate Identifier 2015-NM-141-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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as widespread fatigue damage (WFD). As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. An evaluation by the DAH indicated that the upper chords of the upper deck floor beams are subject to WFD. The inspections and replacement in this proposed AD were developed to support the airplane's LOV of the engineering data that support the established structural maintenance program. We are proposing this AD to detect and correct fatigue cracking of the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. Other Relevant Rulemaking On September 28, 2005, we issued AD 2005-20-29, Amendment 39-14326 (70 FR 59246, October 12, 2005), for certain Boeing Model 747-100, 747- 100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes. AD 2005-20-29 requires repetitive inspections to detect cracks in various areas of the upper deck floor beams, and repair if necessary. AD 2005-20-29 resulted from fatigue testing that revealed severed upper chords of the upper deck floor beams due to fatigue cracking. We issued AD 2005-20-29, to detect and correct cracking in the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. AD 2005-20-29, Amendment 39-14326 (70 FR 59246, October 12, 2005), refers to Boeing Alert Service Bulletin 747-53A2452, dated April 3, 2003, as the appropriate source of service information for certain inspections. This proposed AD would require new inspections at reduced compliance times, which would end the inspections done using Boeing Alert Service Bulletin 747-53A2452, dated April 3, 2003. Related Service Information Under 1 CFR Part 51 We reviewed the following service information. 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. Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. This service information describes procedures for repetitive open hole or surface high frequency eddy current (HFEC) inspections, as applicable, for cracks at the floor panel attachment fastener holes in certain areas and stations; repetitive surface HFEC inspections for cracks in the upper and lower chords of the upper deck floor beams at permanent fastener locations in certain areas and stations; and related investigative and corrective actions. This service information also describes procedures, for airplanes on which certain repairs or modifications are done, for repetitive open hole or surface HFEC inspections, as applicable, for [[Page 60305]] cracks in the repaired and modified areas; and repair. Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012. This service information describes procedures for repetitive replacement of the upper chords of the upper deck floor beams, including pre-replacement inspections and corrective action, and post- replacement repetitive inspections and repair. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this AD and the Service Information.'' 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-2015-3983. 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 actions, 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. For any repair #10 or repair #13 done as specified in Boeing Alert Service Bulletin 747-53A2452, paragraph (i)(2) of this proposed AD would require that post-repair inspections be done before further flight using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Operators must contact the FAA or Boeing Commercial Airplanes Organization Designation Authorization (ODA) before further flight so that the type of actions and intervals for the post-repair inspections can be determined. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012; and Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012; specify to contact the manufacturer for instructions on how to repair certain conditions, but 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 ODA whom we have authorized to make those findings. Explanation of Compliance Time The compliance time for the installation specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is replaced before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 67 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections specified in Boeing Up to 884 work- $0 $75,140, per $5,034,380, per Alert Service Bulletin hours x $85 per inspection cycle. inspection cycle. 747[dash]53A2452, Revision 1, hour = $75,140, dated July 16, 2012. per inspection cycle. Replacement specified in Boeing Up to 696 work- 0 [1] $59,160, per $3,963,720, per Alert Service Bulletin hours x $85 per replacement. replacement. 747[dash]53A2852, dated June 22, hour = $59,160, 2012. per replacement. Post-replacement inspections Up to 586 work- 0 $49,810, per $3,337,270, per specified in Boeing Alert hours x $85 per inspection cycle. inspection cycle. Service Bulletin hour = $49,810, 747[dash]53A2852, dated June 22, per inspection 2012. cycle. ---------------------------------------------------------------------------------------------------------------- [1] We currently have no specific cost estimates associated with the parts necessary for the proposed replacement. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. [[Page 60306]] 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 adding the following new AD: The Boeing Company: Docket No. FAA-2015-3983; Directorate Identifier 2015-NM-141-AD. (a) Comments Due Date The FAA must receive comments on this AD action by November 20, 2015. (b) Affected ADs This AD affects AD 2005-20-29, Amendment 39-14326 (70 FR 59246, October 12, 2005). (c) Applicability This AD applies to The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012. (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) indicating that the upper chords of the upper deck floor beams are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections of the Upper Chords of the Upper Deck Floor Beams At the applicable times specified in Tables 1 through 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012, except as required by paragraph (l)(1) of this AD: Do the inspections specified in paragraphs (g)(1) and (g)(2) of this AD, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2452, Revision 1, dated July 16, 2012, except as required by paragraph (l)(2) of this AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable times specified in Tables 1 through 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. Do all applicable related investigative and corrective actions before further flight. Doing the inspections required by paragraphs (g)(1) and (g)(2) of this AD terminates the inspections required by paragraphs (m) and (n) of AD 2005-20-29, Amendment 39-14326 (70 FR 59246, October 12, 2005). (1) Do an open hole or surface high frequency eddy current (HFEC) inspection, as applicable, for cracks at the fastener holes of the floor panel attachment in the applicable areas and stations identified in Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. (2) Do a surface HFEC inspection for cracks in the upper and lower chords of the upper deck floor beams at permanent fastener locations in the applicable areas and stations identified in Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. (h) Terminating Modification and Repair for the Inspection Specified in Paragraph (g)(1) of This AD A fastener hole modification or a fastener hole repair in Area 1 or Area 2 as described in Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012, terminates the inspection of the fastener holes of the floor panel attachment required by paragraph (g)(1) of this AD for the repaired or modified area only, provided the modification and repair, including related investigative and corrective actions, are done in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012, except as required by paragraph (l)(2) of this AD. (i) Post Mod/Repair Repetitive Inspections (1) For airplanes on which any fastener hole modification or any fastener hole repair was done as specified in Boeing Alert Service Bulletin 747-53A2452: Except as required by paragraph (i)(2) of this AD, at the applicable times specified in Tables 8 and 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later, do an open hole or surface HFEC inspection, as applicable, for cracks in the repaired and modified areas, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Repeat the applicable inspections thereafter at the times specified in Tables 8 and 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. Doing an inspection required by this paragraph terminates the inspections required by paragraph (p) of AD 2005-20-29, Amendment 39-14326 (70 FR 59246, October 12, 2005). (2) For any repair #10 or repair #13 done as specified in Boeing Alert Service Bulletin 747-53A2452: Before further flight, do post- repair inspections using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (j) Replacement of the Upper Chords of the Upper Deck Floor Beams (Includes Pre-Replacement Inspections) Replace the upper chords of the upper deck floor beams by doing the actions required by paragraphs (j)(1) and (j)(2) of this AD at the times specified in those paragraphs. Accomplishing the replacement required by this paragraph terminates the inspections required by paragraphs (g) and (i) of this AD. (1) Before the accumulation of 30,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, do an open hole HFEC inspection for cracks at certain fastener locations in the floor beam webs and side of body frames, and do a detailed inspection for cracks of any removed part that will be re-installed, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012, except as required by paragraph (l)(2) of this AD. Do all applicable corrective actions before further flight. (2) Before further flight after accomplishing the inspections required by paragraph (j)(1) of this AD, install new upper chords of the upper deck floor beams and reinforcing straps or angles, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012, except as required by paragraph (l)(2) of this AD. (k) Post-Replacement Repetitive Inspections For airplanes on which any replacement required by paragraph (j) or (k)(2)(ii) of this AD is done: At the applicable times specified in Tables 2 through 4 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service [[Page 60307]] Bulletin 747-53A2852, dated June 22, 2012, do HFEC inspections for cracks at the permanent fastener holes and the upper chords of the upper deck floor beams, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. (1) If any cracking is found during any inspection required by paragraph (k) or (k)(2)(i) of this AD, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (2) If no cracking is found during any inspection required by the introductory text of paragraph (k) or (k)(2)(i) of this AD, do the actions required by paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. (i) Repeat the inspections specified in paragraph (k) of this AD thereafter at the applicable times specified in Tables 8 and 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012. (ii) Within 10,000 flight cycles after accomplishing the initial HFEC inspections required by paragraph (k) of this AD, replace the upper chords of the upper deck floor beams by doing the actions specified in paragraphs (j)(1) and (j)(2) of this AD. (l) Exceptions to Service Information (1) Where Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012, specifies a compliance time ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012; or Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012; specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (m) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g), (h), and (i) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747-53A2452, dated April 3, 2003, which was incorporated by reference in AD 2005-20-29, Amendment 39-14326 (70 FR 59246, October 12, 2005). (n) Special Flight Permit Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (o) 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 (p)(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. (p) Related Information (1) For more information about this AD, contact Roger Caldwell, Aerospace Engineer, Technical Operations Center, ANM-100D, FAA, Denver Aircraft Certification Office, 26805 East 68th Avenue, Room 214, Denver, CO 80249; phone: 303-342-1086; fax: 303-342-1088; email: [email protected]. (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 September 27, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-25272 Filed 10-5-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 193 / Tuesday, October 6, 2015 / Proposed Rules 60303
plan that reflects maximum practicable subcontractors at all tiers comply with replacement inspections and corrective
opportunities for small businesses in the the requirements and goals set forth in action if necessary; and post-
performance of the contract as the plan established in accordance with replacement repetitive inspections and
subcontractors or suppliers at all tiers of paragraph (c)(1)(x) of this section, repair if necessary. We are proposing
performance. * * * including the establishment of source this AD to detect and correct fatigue
* * * * * lists of small business concerns, small cracking of the upper chords of the
(v) The contractor must assign to the business concerns owned and upper deck floor beams. Undetected
solicitation and the resulting controlled by veterans, small business cracking could result in large deflection
subcontract the NAICS code and concerns owned and controlled by or deformation of the upper deck floor
corresponding size standard that best service-disabled veterans, qualified beams, resulting in damage to wire
describes the principal purpose of the HUBZone small business concerns, bundles and control cables for the flight
subcontract (see § 121.410 of this small business concerns owned and control system, and reduced
chapter). The prime contractor may rely controlled by socially and economically controllability of the airplane. Multiple
on a subcontractor’s electronic disadvantaged individuals, and small adjacent severed floor beams could
representations and certifications, if the business concerns owned and result in rapid decompression of the
solicitation for the subcontract contains controlled by women, and the efforts to airplane.
a clause which provides that the identify and award subcontracts to such DATES: We must receive comments on
subcontractor verifies by submission of small business concerns. this proposed AD by November 20,
the offer that the size or socioeconomic * * * * * 2015.
representations and certifications are Dated: September 28, 2015. ADDRESSES: You may send comments,
current, accurate and complete as of the
Maria Contreras-Sweet, using the procedures found in 14 CFR
date of the offer for the subcontract.
Administrator. 11.43 and 11.45, by any of the following
Electronic submission may include any
[FR Doc. 2015–25234 Filed 10–5–15; 8:45 am] methods:
method acceptable to the prime
• Federal eRulemaking Portal: Go to
contractor including, but not limited to, BILLING CODE 8025–01–P
http://www.regulations.gov. Follow the
size or socioeconomic representations
instructions for submitting comments.
and certifications made in SAM (or any • Fax: 202–493–2251.
successor system). A prime contractor or DEPARTMENT OF TRANSPORTATION • Mail: U.S. Department of
subcontractor may not require the use of Transportation, Docket Operations, M–
SAM (or any successor system) for Federal Aviation Administration
30, West Building Ground Floor, Room
purposes of representing size or W12–140, 1200 New Jersey Avenue SE.,
socioeconomic status in connection 14 CFR Part 39
Washington, DC 20590.
with a subcontract; [Docket No. FAA–2015–3983; Directorate • Hand Delivery: Deliver to Mail
* * * * * Identifier 2015–NM–141–AD] address above between 9 a.m. and 5
(x) The prime contractor must require p.m., Monday through Friday, except
all subcontractors (except small RIN 2120–AA64
Federal holidays.
business concerns) who receive Airworthiness Directives; The Boeing For service information identified in
subcontracts in excess of $1,500,000 in Company Airplanes this proposed AD, contact Boeing
the case of a subcontract for the Commercial Airplanes, Attention: Data
construction of any public facility, or in AGENCY: Federal Aviation & Services Management, P.O. Box 3707,
excess of $650,000 in the case of all Administration (FAA), DOT. MC 2H–65, Seattle, WA 98124–2207;
other subcontracts, and which offer ACTION: Notice of proposed rulemaking telephone 206–544–5000, extension 1;
further subcontracting possibilities, to (NPRM). fax 206–766–5680; Internet https://
adopt a subcontracting plan of its own www.myboeingfleet.com. You may view
consistent with this section, and must SUMMARY: We propose to adopt a new this referenced service information at
ensure at a minimum that all airworthiness directive (AD) for certain the FAA, Transport Airplane
subcontractors required to maintain The Boeing Company Model 747–100, Directorate, 1601 Lind Avenue SW.,
subcontracting plans pursuant to this 747–100B, 747–100B SUD, 747–200B, Renton, WA. For information on the
paragraph, will review and approve 747–300, 747SR, and 747SP series availability of this material at the FAA,
subcontracting plans submitted by their airplanes. This proposed AD was call 425–227–1221. It is also available
subcontractors; monitor subcontractor prompted by an evaluation by the on the Internet at http://
compliance with their approved design approval holder (DAH) www.regulations.gov by searching for
subcontracting plans; ensure that indicating that the upper chords of the and locating Docket No. FAA–2015–
subcontracting reports are submitted by upper deck floor beams are subject to 3983.
their subcontractors when required; widespread fatigue damage (WFD). This
acknowledge receipt of their proposed AD would require repetitive Examining the AD Docket
subcontractors’ reports; compare the inspections for cracks at the floor panel You may examine the AD docket on
performance of their subcontractors to attachment fastener holes; repetitive the Internet at http://
subcontracting plans and goals; and inspections for cracks in the upper and www.regulations.gov by searching for
discuss performance with lower chords of the upper deck floor and locating Docket No. FAA–2015–
rmajette on DSK7SPTVN1PROD with PROPOSALS
subcontractors when necessary to beams at permanent fastener locations; 3983; or in person at the Docket
ensure their subcontractors make a good repetitive inspections for cracks in Management Facility between 9 a.m.
faith effort to comply with their certain repaired and modified areas; and and 5 p.m., Monday through Friday,
subcontracting plans; and related investigative and corrective except Federal holidays. The AD docket
(xi) The prime contractor must recite actions if necessary. This proposed AD contains this proposed AD, the
the types of records the prime will would also require repetitive regulatory evaluation, any comments
maintain to demonstrate procedures replacement of the upper chords of the received, and other information. The
which have been adopted to ensure upper deck floor beams, including pre- street address for the Docket Office
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cracks in the repaired and modified follow-on actions that (1) are related to specify to contact the manufacturer for
areas; and repair. the primary actions, and (2) further instructions on how to repair certain
• Boeing Alert Service Bulletin 747– investigate the nature of any condition conditions, but this proposed AD would
53A2852, dated June 22, 2012. This found. Related investigative actions in require repairing those conditions in
service information describes an AD could include, for example, one of the following ways:
procedures for repetitive replacement of inspections. • In accordance with a method that
the upper chords of the upper deck floor The phrase ‘‘corrective actions’’ is we approve; or
beams, including pre-replacement used in this proposed AD. ‘‘Corrective • Using data that meet the
inspections and corrective action, and actions’’ are actions that correct or certification basis of the airplane, and
post-replacement repetitive inspections address any condition found. Corrective that have been approved by the Boeing
and repair. actions in an AD could include, for Commercial Airplanes ODA whom we
FAA’s Determination example, repairs. have authorized to make those findings.
We are proposing this AD because we For any repair #10 or repair #13 done
Explanation of Compliance Time
evaluated all the relevant information as specified in Boeing Alert Service
Bulletin 747–53A2452, paragraph (i)(2) The compliance time for the
and determined the unsafe condition
of this proposed AD would require that installation specified in this proposed
described previously is likely to exist or
post-repair inspections be done before AD for addressing WFD was established
develop in other products of the same
type design. further flight using a method approved to ensure that discrepant structure is
in accordance with the procedures replaced before WFD develops in
Proposed AD Requirements specified in paragraph (o) of this AD. airplanes. Standard inspection
This proposed AD would require Operators must contact the FAA or techniques cannot be relied on to detect
accomplishing the actions specified in Boeing Commercial Airplanes WFD before it becomes a hazard to
the service information described Organization Designation Authorization flight. We will not grant any extensions
previously, except as discussed under (ODA) before further flight so that the of the compliance time to complete any
‘‘Differences Between this AD and the type of actions and intervals for the AD-mandated service bulletin related to
Service Information.’’ For information post-repair inspections can be WFD without extensive new data that
on the procedures and compliance determined. would substantiate and clearly warrant
times, see this service information at such an extension.
Differences Between This Proposed AD
http://www.regulations.gov by searching and the Service Information Costs of Compliance
for and locating Docket No. FAA–2015–
3983. Boeing Alert Service Bulletin 747– We estimate that this proposed AD
The phrase ‘‘related investigative 53A2452, Revision 1, dated July 16, affects 67 airplanes of U.S. registry.
actions’’ is used in this proposed AD. 2012; and Boeing Alert Service Bulletin We estimate the following costs to
‘‘Related investigative actions’’ are 747–53A2852, dated June 22, 2012; comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections specified in Boe- Up to 884 work-hours × $85 $0 $75,140, per inspection cycle $5,034,380, per inspection
ing Alert Service Bulletin per hour = $75,140, per in- cycle.
747-53A2452, Revision 1, spection cycle.
dated July 16, 2012.
Replacement specified in Up to 696 work-hours × $85 0 [1] $59,160, per replacement ...... $3,963,720, per replacement.
Boeing Alert Service Bul- per hour = $59,160, per re-
letin 747-53A2852, dated placement.
June 22, 2012.
Post-replacement inspections Up to 586 work-hours × $85 0 $49,810, per inspection cycle $3,337,270, per inspection
specified in Boeing Alert per hour = $49,810, per in- cycle.
Service Bulletin spection cycle.
747-53A2852, dated June
22, 2012.
[1] We currently have no specific cost estimates associated with the parts necessary for the proposed replacement.
We have received no definitive data We are issuing this rulemaking under products identified in this rulemaking
that would enable us to provide cost the authority described in Subtitle VII, action.
estimates for the on-condition actions Part A, Subpart III, Section 44701,
Regulatory Findings
specified in this proposed AD. ‘‘General requirements.’’ Under that
section, Congress charges the FAA with We have determined that this
Authority for This Rulemaking
promoting safe flight of civil aircraft in proposed AD would not have federalism
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Title 49 of the United States Code air commerce by prescribing regulations implications under Executive Order
specifies the FAA’s authority to issue for practices, methods, and procedures 13132. This proposed AD would not
rules on aviation safety. Subtitle I, the Administrator finds necessary for have a substantial direct effect on the
Section 106, describes the authority of safety in air commerce. This regulation States, on the relationship between the
the FAA Administrator. Subtitle VII, is within the scope of that authority national Government and the States, or
Aviation Programs, describes in more because it addresses an unsafe condition on the distribution of power and
detail the scope of the Agency’s that is likely to exist or develop on responsibilities among the various
authority. levels of government.
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![60306 Federal Register / Vol. 80, No. 193 / Tuesday, October 6, 2015 / Proposed Rules
For the reasons discussed above, I bundles and control cables for the flight Bulletin 747–53A2452: Except as required by
certify that the proposed regulation: control system, and reduced controllability of paragraph (i)(2) of this AD, at the applicable
(1) Is not a ‘‘significant regulatory the airplane. Multiple adjacent severed floor times specified in Tables 8 and 9 of
action’’ under Executive Order 12866, beams could result in rapid decompression of paragraph 1.E., ‘‘Compliance,’’ of Boeing
(2) Is not a ‘‘significant rule’’ under the airplane. Alert Service Bulletin 747–53A2452,
Revision 1, dated July 16, 2012, or within
the DOT Regulatory Policies and (f) Compliance
1,000 flight cycles after the effective date of
Procedures (44 FR 11034, February 26, Comply with this AD within the this AD, whichever occurs later, do an open
1979), compliance times specified, unless already hole or surface HFEC inspection, as
(3) Will not affect intrastate aviation done. applicable, for cracks in the repaired and
in Alaska, and (g) Repetitive Inspections of the Upper modified areas, in accordance with the
(4) Will not have a significant Chords of the Upper Deck Floor Beams Accomplishment Instructions of Boeing Alert
economic impact, positive or negative, Service Bulletin 747–53A2452, Revision 1,
on a substantial number of small entities At the applicable times specified in Tables dated July 16, 2012. If any cracking is found,
1 through 7 of paragraph 1.E., ‘‘Compliance,’’ before further flight, repair using a method
under the criteria of the Regulatory of Boeing Alert Service Bulletin 747–
Flexibility Act. approved in accordance with the procedures
53A2452, Revision 1, dated July 16, 2012, specified in paragraph (o) of this AD. Repeat
List of Subjects in 14 CFR Part 39 except as required by paragraph (l)(1) of this the applicable inspections thereafter at the
AD: Do the inspections specified in times specified in Tables 8 and 9 of
Air transportation, Aircraft, Aviation paragraphs (g)(1) and (g)(2) of this AD, and paragraph 1.E., ‘‘Compliance,’’ of Boeing
safety, Incorporation by reference, do all applicable related investigative and Alert Service Bulletin 747–53A2452,
Safety. corrective actions, in accordance with the Revision 1, dated July 16, 2012. Doing an
Accomplishment Instructions of Boeing Alert inspection required by this paragraph
The Proposed Amendment Service Bulletin 747–53A2452, Revision 1, terminates the inspections required by
Accordingly, under the authority dated July 16, 2012, except as required by
paragraph (p) of AD 2005–20–29,
delegated to me by the Administrator, paragraph (l)(2) of this AD. Repeat the
Amendment 39–14326 (70 FR 59246, October
inspections specified in paragraphs (g)(1) and
the FAA proposes to amend 14 CFR part (g)(2) of this AD thereafter at the applicable
12, 2005).
39 as follows: (2) For any repair #10 or repair #13 done
times specified in Tables 1 through 7 of
as specified in Boeing Alert Service Bulletin
paragraph 1.E., ‘‘Compliance,’’ of Boeing
PART 39—AIRWORTHINESS 747–53A2452: Before further flight, do post-
Alert Service Bulletin 747–53A2452,
DIRECTIVES repair inspections using a method approved
Revision 1, dated July 16, 2012. Do all
in accordance with the procedures specified
applicable related investigative and
■ 1. The authority citation for part 39 in paragraph (o) of this AD.
corrective actions before further flight. Doing
continues to read as follows: the inspections required by paragraphs (g)(1) (j) Replacement of the Upper Chords of the
Authority: 49 U.S.C. 106(g), 40113, 44701. and (g)(2) of this AD terminates the Upper Deck Floor Beams (Includes Pre-
inspections required by paragraphs (m) and Replacement Inspections)
§ 39.13 [Amended] (n) of AD 2005–20–29, Amendment 39–
Replace the upper chords of the upper
■ 2. The FAA amends § 39.13 by adding 14326 (70 FR 59246, October 12, 2005).
deck floor beams by doing the actions
(1) Do an open hole or surface high
the following new AD: frequency eddy current (HFEC) inspection, as
required by paragraphs (j)(1) and (j)(2) of this
AD at the times specified in those
The Boeing Company: Docket No. FAA– applicable, for cracks at the fastener holes of
paragraphs. Accomplishing the replacement
2015–3983; Directorate Identifier 2015– the floor panel attachment in the applicable
required by this paragraph terminates the
NM–141–AD. areas and stations identified in Boeing Alert
Service Bulletin 747–53A2452, Revision 1, inspections required by paragraphs (g) and (i)
(a) Comments Due Date dated July 16, 2012. of this AD.
The FAA must receive comments on this (2) Do a surface HFEC inspection for cracks (1) Before the accumulation of 30,000 total
AD action by November 20, 2015. in the upper and lower chords of the upper flight cycles, or within 3,000 flight cycles
deck floor beams at permanent fastener after the effective date of this AD, whichever
(b) Affected ADs occurs later, do an open hole HFEC
locations in the applicable areas and stations
This AD affects AD 2005–20–29, identified in Boeing Alert Service Bulletin inspection for cracks at certain fastener
Amendment 39–14326 (70 FR 59246, October 747–53A2452, Revision 1, dated July 16, locations in the floor beam webs and side of
12, 2005). 2012. body frames, and do a detailed inspection for
cracks of any removed part that will be re-
(c) Applicability (h) Terminating Modification and Repair for installed, and do all applicable corrective
This AD applies to The Boeing Company the Inspection Specified in Paragraph (g)(1) actions, in accordance with the
Model 747–100, 747–100B, 747–100B SUD, of This AD Accomplishment Instructions of Boeing Alert
747–200B, 747–300, 747SR, and 747SP series A fastener hole modification or a fastener Service Bulletin 747–53A2852, dated June
airplanes; certificated in any category; as hole repair in Area 1 or Area 2 as described 22, 2012, except as required by paragraph
identified in Boeing Alert Service Bulletin in Boeing Alert Service Bulletin 747– (l)(2) of this AD. Do all applicable corrective
747–53A2852, dated June 22, 2012. 53A2452, Revision 1, dated July 16, 2012, actions before further flight.
terminates the inspection of the fastener (2) Before further flight after accomplishing
(d) Subject the inspections required by paragraph (j)(1)
holes of the floor panel attachment required
Air Transport Association (ATA) of by paragraph (g)(1) of this AD for the repaired of this AD, install new upper chords of the
America Code 53, Fuselage. or modified area only, provided the upper deck floor beams and reinforcing
modification and repair, including related straps or angles, in accordance with the
(e) Unsafe Condition Accomplishment Instructions of Boeing Alert
investigative and corrective actions, are done
This AD was prompted by an evaluation by in accordance with the Accomplishment Service Bulletin 747–53A2852, dated June
rmajette on DSK7SPTVN1PROD with PROPOSALS
the design approval holder (DAH) indicating Instructions of Boeing Alert Service Bulletin 22, 2012, except as required by paragraph
that the upper chords of the upper deck floor 747–53A2452, Revision 1, dated July 16, (l)(2) of this AD.
beams are subject to widespread fatigue 2012, except as required by paragraph (l)(2)
damage (WFD). We are issuing this AD to (k) Post-Replacement Repetitive Inspections
of this AD.
detect and correct fatigue cracking of the For airplanes on which any replacement
upper chords of the upper deck floor beams. (i) Post Mod/Repair Repetitive Inspections required by paragraph (j) or (k)(2)(ii) of this
Undetected cracking could result in large (1) For airplanes on which any fastener AD is done: At the applicable times specified
deflection or deformation of the upper deck hole modification or any fastener hole repair in Tables 2 through 4 in paragraph 1.E.,
floor beams, resulting in damage to wire was done as specified in Boeing Alert Service ‘‘Compliance,’’ of Boeing Alert Service
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Bulletin 747–53A2852, dated June 22, 2012, paragraph (p)(1) of this AD. Information may AD would require a detailed inspection
do HFEC inspections for cracks at the be emailed to: 9-ANM-Seattle-ACO-AMOC- for any distress of the vertical stabilizer
permanent fastener holes and the upper Requests@faa.gov. leading edge skin, and related
chords of the upper deck floor beams, in (2) Before using any approved AMOC,
notify your appropriate principal inspector,
investigative and corrective actions, if
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin or lacking a principal inspector, the manager necessary. This proposed AD would
747–53A2452, Revision 1, dated July 16, of the local flight standards district office/ also require, for certain airplanes,
2012. certificate holding district office. repetitive detailed inspections of the
(1) If any cracking is found during any (3) An AMOC that provides an acceptable spar cap for any loose and missing
inspection required by paragraph (k) or level of safety may be used for any repair fasteners, repetitive high frequency
(k)(2)(i) of this AD, before further flight, required by this AD if it is approved by the eddy current (HFEC) and radiographic
repair using a method approved in Boeing Commercial Airplanes Organization testing (RT) inspections of the spar cap
accordance with the procedures specified in Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
for any crack, and related investigative
paragraph (o) of this AD.
(2) If no cracking is found during any ACO, to make those findings. For a repair and corrective actions, if necessary. We
inspection required by the introductory text method to be approved, the repair must meet are proposing this AD to detect and
of paragraph (k) or (k)(2)(i) of this AD, do the the certification basis of the airplane, and the correct any crack in the vertical
actions required by paragraphs (k)(2)(i) and approval must specifically refer to this AD. stabilizer leading edge and front spar
(k)(2)(ii) of this AD. cap, which may result in the structure
(p) Related Information
(i) Repeat the inspections specified in becoming unable to support limit load,
paragraph (k) of this AD thereafter at the (1) For more information about this AD,
and may lead to the loss of the vertical
applicable times specified in Tables 8 and 9 contact Roger Caldwell, Aerospace Engineer,
Technical Operations Center, ANM–100D, stabilizer.
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2452, FAA, Denver Aircraft Certification Office, DATES: We must receive comments on
Revision 1, dated July 16, 2012. 26805 East 68th Avenue, Room 214, Denver, this proposed AD by November 20,
(ii) Within 10,000 flight cycles after CO 80249; phone: 303–342–1086; fax: 303– 2015.
accomplishing the initial HFEC inspections 342–1088; email: roger.caldwell@faa.gov.
required by paragraph (k) of this AD, replace (2) For service information identified in ADDRESSES: You may send comments,
the upper chords of the upper deck floor this AD, contact Boeing Commercial using the procedures found in 14 CFR
beams by doing the actions specified in Airplanes, Attention: Data & Services 11.43 and 11.45, by any of the following
paragraphs (j)(1) and (j)(2) of this AD. Management, P. O. Box 3707, MC 2H–65, methods:
Seattle, WA 98124–2207; telephone 206– • Federal eRulemaking Portal: Go to
(l) Exceptions to Service Information 544–5000, extension 1; fax 206–766–5680; http://www.regulations.gov. Follow the
(1) Where Boeing Alert Service Bulletin Internet https://www.myboeingfleet.com. You instructions for submitting comments.
747–53A2452, Revision 1, dated July 16, may view this referenced service information • Fax: 202–493–2251.
2012, specifies a compliance time ‘‘after the at the FAA, Transport Airplane Directorate,
Revision 1 date of this service bulletin,’’ this
• Mail: U.S. Department of
1601 Lind Avenue SW., Renton, WA. For
AD requires compliance within the specified Transportation, Docket Operations, M–
information on the availability of this
compliance time after the effective date of material at the FAA, call 425–227–1221. 30, West Building Ground Floor, Room
this AD. W12–140, 1200 New Jersey Avenue SE.,
(2) Where Boeing Alert Service Bulletin Issued in Renton, Washington, on Washington, DC 20590.
747–53A2452, Revision 1, dated July 16, September 27, 2015. • Hand Delivery: Deliver to Mail
2012; or Boeing Alert Service Bulletin 747– Michael Kaszycki, address above between 9 a.m. and 5
53A2852, dated June 22, 2012; specifies to p.m., Monday through Friday, except
contact Boeing for appropriate action: Before Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service. Federal holidays.
further flight, repair using a method
approved in accordance with the procedures [FR Doc. 2015–25272 Filed 10–5–15; 8:45 am] For service information identified in
specified in paragraph (o) of this AD. BILLING CODE 4910–13–P
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
(m) Credit for Previous Actions & Services Management, 3855
This paragraph provides credit for the DEPARTMENT OF TRANSPORTATION Lakewood Boulevard, MC D800–0019,
actions required by paragraphs (g), (h), and Long Beach, CA 90846–0001; telephone:
(i) of this AD, if those actions were performed Federal Aviation Administration 206–544–5000, extension 2; fax: 206–
before the effective date of this AD using
Boeing Alert Service Bulletin 747–53A2452,
766–5683; Internet https://
dated April 3, 2003, which was incorporated 14 CFR Part 39 www.myboeingfleet.com. You may view
by reference in AD 2005–20–29, Amendment [Docket No. FAA–2015–3982; Directorate
this referenced service information at
39–14326 (70 FR 59246, October 12, 2005). Identifier 2015–NM–098–AD] the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
(n) Special Flight Permit RIN 2120–AA64 Renton, WA. For information on the
Special flight permits, as described in availability of this material at the FAA,
Section 21.197 and Section 21.199 of the Airworthiness Directives; The Boeing call 425–227–1221. It is also available
Federal Aviation Regulations (14 CFR 21.197 Company Airplanes
and 21.199), are not allowed. on the Internet at http://
AGENCY: Federal Aviation www.regulations.gov by searching for
(o) Alternative Methods of Compliance Administration (FAA), DOT. and locating Docket No. FAA–2015–
(AMOCs) 3982.
ACTION: Notice of proposed rulemaking
(1) The Manager, Seattle Aircraft (NPRM).
rmajette on DSK7SPTVN1PROD with PROPOSALS
Certification Office (ACO), FAA, has the Examining the AD Docket
authority to approve AMOCs for this AD, if SUMMARY: We propose to adopt a new You may examine the AD docket on
requested using the procedures found in 14 airworthiness directive (AD) for certain the Internet at http://
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
The Boeing Company Model 717–200 www.regulations.gov by searching for
or local Flight Standards District Office, as airplanes. This proposed AD was and locating Docket No. FAA–2015–
appropriate. If sending information directly prompted by multiple reports of the 3982; or in person at the Docket
to the manager of the ACO, send it to the vertical stabilizer leading edge showing Management Facility between 9 a.m.
attention of the person identified in signs of fastener distress. This proposed and 5 p.m., Monday through Friday,
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Document Created: 2015-12-15 08:50:48
Document Modified: 2015-12-15 08:50:48
| 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 November 20, 2015. | |
| Contact | Roger Caldwell, Aerospace Engineer, Technical Operations Center, ANM-100D, FAA, Denver Aircraft Certification Office, 26805 East 68th Avenue, Room 214, Denver, CO 80249; phone: 303-342-1086; fax: 303-342-1088; email: [email protected] | |
| FR Citation | 80 FR 60303 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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