81 FR 62031 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 174 (September 8, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 174 (September 8, 2016)
| Page Range | 62031-62035 | |
| FR Document | 2016-21147 |
[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)] [Proposed Rules] [Pages 62031-62035] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-21147] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9067; Directorate Identifier 2016-NM-043-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 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. This proposed AD was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective and a structural reevaluation by the manufacturer that identified additional structural elements that qualify as structural significant items (SSIs). This proposed AD would require revising the maintenance or inspection program, as applicable, to include inspections that will give no less than the required damage tolerance rating (DTR) for certain SSIs, and repairing any cracked structure. This proposed AD would also require inspections to detect cracks of all SSI structure, and repair if necessary. We are proposing this AD to ensure the continued structural integrity of 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. DATES: We must receive comments on this proposed AD by October 24, 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 NPRM, 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. 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-2016- 9067; 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 62032]] (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 (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6428; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9067; Directorate Identifier 2016-NM-043-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 December 26, 2007, we issued AD 2004-07-22 R1, Amendment 39- 15326 (73 FR 1052, January 7, 2008); corrected February 14, 2008 (73 FR 8589) (``AD 2004-07-22 R1''); 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 2004-07-22 R1 requires that the maintenance inspection program be revised to include inspections that will give no less than the required DTR for each SSI, and repair of cracked structure. AD 2004-07-22 R1 was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective. We issued AD 2004-07-22 R1 to ensure the continued structural integrity of all Boeing 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. Actions Since AD 2004-07-22 R1 Was Issued Since we issued AD 2004-07-22 R1, a structural reevaluation by the manufacturer identified additional structural elements that qualify as SSIs. We have determined that supplemental inspections are required for timely detection of fatigue cracking for these additional structural elements. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013. The service information describes procedures for inspections to detect cracks of all structure identified as SSIs and includes six new SSIs since the last revision. We also reviewed Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015. The service information describes procedures for inspections of wing, fuselage, and empennage SSIs for Model 747-400 LCF airplanes. 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. 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 revising the maintenance or inspection program, as applicable, to include inspections that will give no less than the required DTR for certain SSIs, and repairing any cracked structure. This proposed AD would also require inspections to detect cracks of all SSI structure, and repair if necessary. This proposed AD does not supersede 2004-07-22 R1. However, accomplishing the revision specified in paragraph (h) of this proposed AD would terminate the requirements of paragraphs (f), (g), and (h) of AD 2004-07-22 R1. Also, doing an inspection specified in paragraph (i) of this proposed AD would terminate the corresponding inspection required by paragraph (i) of AD 2004-07-22 R1. Costs of Compliance We estimate that this proposed AD affects 118 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Revision of maintenance or 1 work-hour x $85 per $0 $85 $10,030 inspection program. hour = $85. ---------------------------------------------------------------------------------------------------------------- We have not specified cost estimates for the inspection and repair specified in this proposed AD. Compliance with this proposed AD constitutes a method of compliance with the FAA aging airplane safety final rule (AASFR) (70 FR 5518, February 2, 2005) for certain baseline structure of 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. The AASFR requires certain operators to incorporate damage tolerance inspections into their maintenance inspection programs. These requirements are described in 14 CFR 121.1109(c)(1) and 14 CFR 129.109(b)(1). Accomplishment of the actions specified in this proposed AD will meet the requirements of these regulations for certain baseline structure. The costs for accomplishing the inspection portion of this proposed AD were accounted for in the regulatory evaluation of the AASFR. 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. [[Page 62033]] 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 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 this 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 airworthiness directive (AD): The Boeing Company: Docket No. FAA-2016-9067; Directorate Identifier 2016-NM-043-AD. (a) Comments Due Date We must receive comments by October 24, 2016. (b) Affected ADs This AD affects AD 2004-07-22 R1, Amendment 39-15326 (73 FR 1052, January 7, 2008); corrected February 14, 2008 (73 FR 8589) (``AD 2004-07-22 R1''). (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. Note 1 to paragraph (c) of this AD: A Model 747-400 LCF airplane is a Model 747-400 series airplane that has been modified from a passenger airplane to a freighter configuration as specified in Boeing Service Bulletin 747-00-2084. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage; 54, Nacelles/Pylons; 55, Stabilizers; 57, Wings. (e) Unsafe Condition This AD was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective and a structural reevaluation by the manufacturer that identified additional structural elements that qualify as structural significant items (SSIs). We are issuing this AD to ensure the continued structural integrity of 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. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of SSI For the purposes of this AD, an SSI is defined as a principal structural element (PSE). A PSE is a structural element that contributes significantly to the carrying of flight, ground, or pressurization loads, and whose integrity is essential in maintaining the overall structural integrity of the airplane. (h) Maintenance or Inspection Program Revision for All Airplanes Prior to reaching the compliance thresholds specified in paragraph (i)(1)(i), (i)(2)(i), (j)(1)(i), or (j)(2)(i) of this AD, as applicable, or within 12 months after the effective date of this AD, whichever occurs later: Incorporate a revision into the maintenance or inspection program, as applicable, that provides no less than the required damage tolerance rating (DTR) for each SSI listed in the applicable service information specified in paragraph (h)(1) or (h)(2) of this AD. The revision to the maintenance or inspection program must include, and must be implemented in accordance with, the procedures in Section 5.0, ``Damage Tolerance Rating (DTR) System Application,'' of Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013; and Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015; as applicable. Accomplishing the revision required by this paragraph terminates the actions required by paragraphs (f), (g), and (h) of AD 2004-07-22 R1. After accomplishing the revision required by this paragraph, the revisions required by paragraphs (f), (g), and (h) of AD 2004-07-22 R1, as applicable, must be removed. (1) For all airplanes except Model 747-400 LCF airplanes: SSIs listed in Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013. (2) For Model 747-400 LCF airplanes: SSIs listed in Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013; and SSIs listed in Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015. For SSIs listed in both Boeing Document No. D6-35022- 1, ``747-400 LCF Supplemental Structural Inspection Document-- Appendix A,'' dated November 2015; and Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013: Incorporate the SSIs listed Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015. (i) Inspection Compliance Times for All Model 747 Airplanes Except Model 747-400 LCF airplanes For all Model 747 airplanes except Model 747-400 LCF airplanes: Perform inspections to detect cracks of all structure identified in Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013, at the times specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable. Once the initial inspection has been performed, in order to remain in compliance with the maintenance or inspection program, as required by paragraph (h) of this AD, repetitive inspections are required at the intervals specified in Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013. Doing an inspection required by this paragraph terminates the corresponding inspection required by paragraph (i) of AD 2004-07-22 R1. (1) For wing structure, except as provided by paragraph (i)(3) of this AD: Inspect at the times specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, whichever occurs later. (i) Within the applicable compliance time specified in paragraph (i)(1)(i)(A) or (i)(1)(i)(B) of this AD. [[Page 62034]] (A) For all Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes: Prior to the accumulation of 20,000 total flight cycles or 100,000 total flight hours, whichever occurs first. (B) For all Model 747-400, 747-400D, and 747-400F series airplanes: Prior to the accumulation of 20,000 total flight cycles or 115,000 total flight hours, whichever occurs first. (ii) Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs later. (2) For all structure other than wing structure, except as provided by paragraph (i)(3) of this AD: At the time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD, whichever occurs later. (i) Prior to the accumulation of 20,000 total flight cycles. (ii) Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs later. (3) For any portion of an SSI that has been replaced with new structure: Inspect at the later of the times specified in paragraphs (i)(3)(i) and (i)(3)(ii) of this AD. (i) At the time specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. (ii) Within 10,000 flight cycles after the replacement of the part with a new part. (j) Inspection Compliance Times for Model 747-400 LCF Airplanes For Model 747-400 LCF airplanes: Perform inspections to detect cracks of all structure identified in Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013; and Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015; at the times specified in paragraph (j)(1) or (j)(2) of this AD, as applicable. Once the initial inspection has been performed, in order to remain in compliance with the maintenance or inspection program, as required by paragraph (h) of this AD, repetitive inspections are required at the intervals specified in Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013; and Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015. Where SSIs are listed in both Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013; and Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015; the SSIs listed in Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015, take precedence. Doing an inspection required by this paragraph terminates the corresponding inspection required by paragraph (i) of AD 2004-07-22 R1. (1) For wing structure: Inspect at the times specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, whichever occurs later. (i) Prior to the accumulation of 20,000 total flight cycles or 115,000 total flight hours, whichever occurs first. (ii) Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs later. (2) For all structure other than wing structure: At the time specified in paragraph (j)(2)(i) or (i)(2)(ii) of this AD, whichever occurs later. (i) At the earlier of the times specified in paragraphs (j)(2)(i)(A) and (j)(2)(i)(B) of this AD. (A) Prior to the accumulation of 20,000 total flight cycles. (B) Within the applicable initial compliance time specified in Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013; and Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015. Where SSIs are listed in both Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013; and Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015; the SSIs listed in Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015, take precedence. (ii) Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs later. (k) Repair If any cracked structure is found during any inspection required by paragraph (i) or (j) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Inspection Program for Transferred Airplanes Before any airplane that is subject to this AD and that has exceeded the applicable compliance times specified in paragraph (i) or (j) of this AD can be added to an air carrier's operations specifications, a program for the accomplishment of the inspections required by this AD must be established in accordance with paragraph (l)(1) or (l)(2) of this AD, as applicable. (1) For airplanes that have been inspected as specified in this AD, the inspection of each SSI must be accomplished by the new operator using the previous operator's schedule and inspection method, or the new operator's schedule and inspection method, at whichever time would result in the earlier accomplishment for that SSI inspection. The compliance time for accomplishment of this inspection must be measured from the last inspection accomplished by the previous operator. After each inspection has been performed once, each subsequent inspection must be performed using the new operator's schedule and inspection method. (2) For airplanes that have not been inspected as specified in this AD, the inspection of each SSI required by this AD must be accomplished either prior to adding the airplane to the air carrier's operations specification, or using a schedule and an inspection method approved by the Manager, Seattle Aircraft Certification Office (ACO). After each inspection has been performed once, each subsequent inspection must be performed using the new operator's schedule and inspection method. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (n)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO- AMOC-Requests@faa. (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, modification, or alteration 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. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2004-07-22 R1 are approved as AMOCs for the corresponding provisions of paragraphs (h), (i), and (j) of this AD for the SSIs identified in the AMOC, except for any SSI that has an expanded inspection area identified in Boeing Document No. D6-35022, ``Supplemental Structural Inspection Document for Model 747 Airplanes,'' Revision H, dated September 2013; or Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection Document--Appendix A,'' dated November 2015. (n) 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: [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. [[Page 62035]] Issued in Renton, Washington, on August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-21147 Filed 9-7-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules 62031
Airworthiness Limitations Section inspection inspector, the manager of the local flight or have exceeded their design service
is insufficient to detect early crack standards district office/certificate holding objective and a structural reevaluation
development. We are issuing this AD to district office. The AMOC approval letter by the manufacturer that identified
detect and correct cracks in the fuselage skin; must specifically reference this AD.
(2) Contacting the Manufacturer: For any
additional structural elements that
such cracking could result in reduced
structural integrity of the fuselage. requirement in this AD to obtain corrective qualify as structural significant items
actions from a manufacturer, the action must (SSIs). This proposed AD would require
(f) Compliance be accomplished using a method approved revising the maintenance or inspection
Comply with this AD within the by the Manager, International Branch, ANM– program, as applicable, to include
compliance times specified, unless already 116, Transport Airplane Directorate, FAA; or inspections that will give no less than
done. EASA; or Fokker Services B.V.’s EASA the required damage tolerance rating
Design Organization Approval (DOA). If (DTR) for certain SSIs, and repairing any
(g) Inspection
approved by the DOA, the approval must
Within the compliance time specified in cracked structure. This proposed AD
include the DOA-authorized signature.
paragraphs (g)(1) and (g)(2) of this AD, as would also require inspections to detect
applicable, do high and low frequency eddy (j) Related Information cracks of all SSI structure, and repair if
current inspections for cracks in the fuselage (1) Refer to Mandatory Continuing necessary. We are proposing this AD to
skin around the largest traffic collision Airworthiness Information (MCAI) EASA ensure the continued structural integrity
avoidance system (TCAS) antenna external Airworthiness Directive 2016–0029, dated of all The Boeing Company Model 747–
doubler and of the longitudinal lap joint at February 23, 2016, for related information. 100, 747–100B, 747–100B SUD, 747–
fuselage stringer STR37 between fuselage This MCAI may be found in the AD docket
station (STA) STA6805 and STA7305, in
200B, 747–200C, 747–200F, 747–300,
on the Internet at http://www.regulations.gov
accordance with the Accomplishment 747–400, 747–400D, 747–400F, 747SR,
by searching for and locating Docket No.
Instructions of Fokker Service Bulletin FAA–2016–9058. and 747SP series airplanes.
SBF100–53–130, dated December 01, 2015. (2) For service information identified in DATES: We must receive comments on
(1) For airplanes having 45,000 or more this AD, contact Fokker Services B.V., this proposed AD by October 24, 2016.
flight cycles as of the effective date of this Technical Services Dept., P.O. Box 1357, ADDRESSES: You may send comments,
AD, since the date of issuance of the original 2130 EL Hoofddorp, the Netherlands;
airworthiness certificate or the date of using the procedures found in 14 CFR
telephone: +31 (0)88–6280–350; fax: +31
issuance of the original export certificate of (0)88–6280–111; email: technicalservices@
11.43 and 11.45, by any of the following
airworthiness: Do the high and low frequency fokker.com; Internet http://www.myfokker methods:
eddy current inspections within 750 flight fleet.com. You may view this service • Federal eRulemaking Portal: Go to
cycles after the effective date of this AD. information at the FAA, Transport Airplane http://www.regulations.gov. Follow the
(2) For airplanes having 40,000 or more Directorate, 1601 Lind Avenue SW., Renton, instructions for submitting comments.
flight cycles, but less than 45,000 flight WA. For information on the availability of • Fax: 202–493–2251.
cycles as of the effective date of this AD,
since the date of issuance of the original
this material at the FAA, call 425–227–1221. • Mail: U.S. Department of
airworthiness certificate or the date of Issued in Renton, Washington, on August Transportation, Docket Operations, M–
issuance of the original export certificate of 24, 2016. 30, West Building Ground Floor, Room
airworthiness: Do the high and low frequency John P. Piccola, Jr., W12–140, 1200 New Jersey Avenue SE.,
eddy current inspections within 1,500 flight Acting Manager, Transport Airplane Washington, DC 20590.
cycles after the effective date of this AD. Directorate, Aircraft Certification Service. • Hand Delivery: Deliver to Mail
(h) Corrective Action [FR Doc. 2016–21151 Filed 9–7–16; 8:45 am] address above between 9 a.m. and 5
p.m., Monday through Friday, except
If any crack is found during any inspection BILLING CODE 4910–13–P
required by paragraph (g) of this AD: Before Federal holidays.
further flight, repair using a method For service information identified in
approved by the Manager, International DEPARTMENT OF TRANSPORTATION this NPRM, contact Boeing Commercial
Branch, ANM 116, Transport Airplane Airplanes, Attention: Data & Services
Directorate, FAA; or the European Aviation Federal Aviation Administration Management, P.O. Box 3707, MC 2H–65,
Safety Agency (EASA); or Fokker B.V. Seattle, WA 98124–2207; telephone
Service’s EASA Design Organization 14 CFR Part 39 206–544–5000, extension 1; fax 206–
Approval (DOA).
766–5680; Internet https://
[Docket No. FAA–2016–9067; Directorate
(i) Other FAA AD Provisions Identifier 2016–NM–043–AD] www.myboeingfleet.com. You may view
The following provisions also apply to this this referenced service information at
AD: RIN 2120–AA64 the FAA, Transport Airplane
(1) Alternative Methods of Compliance Directorate, 1601 Lind Avenue SW.,
(AMOCs): The Manager, International Airworthiness Directives; The Boeing Renton, WA. For information on the
Branch, ANM–116, Transport Airplane Company Airplanes availability of this material at the FAA,
Directorate, FAA, has the authority to call 425–227–1221.
approve AMOCs for this AD, if requested AGENCY: Federal Aviation
using the procedures found in 14 CFR 39.19. Administration (FAA), DOT. Examining the AD Docket
In accordance with 14 CFR 39.19, send your ACTION: Notice of proposed rulemaking
request to your principal inspector or local (NPRM). You may examine the AD docket on
Flight Standards District Office, as the Internet at http://
appropriate. If sending information directly SUMMARY: We propose to adopt a new www.regulations.gov by searching for
to the International Branch, send it to ATTN: airworthiness directive (AD) for all The and locating Docket No. FAA–2016–
mstockstill on DSK3G9T082PROD with PROPOSALS
Tom Rodriguez, Aerospace Engineer, Boeing Company Model 747–100, 747– 9067; or in person at the Docket
International Branch, ANM–116, Transport 100B, 747–100B SUD, 747–200B, 747– Management Facility between 9 a.m.
Airplane Directorate, FAA, 1601 Lind 200C, 747–200F, 747–300, 747–400, and 5 p.m., Monday through Friday,
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149. 747–400D, 747–400F, 747SR, and 747SP except Federal holidays. The AD docket
Information may be emailed to: 9-ANM-116- series airplanes. This proposed AD was contains this proposed AD, the
AMOC-REQUESTS@faa.gov. Before using prompted by a report of incidents regulatory evaluation, any comments
any approved AMOC, notify your appropriate involving fatigue cracking in transport received, and other information. The
principal inspector, or lacking a principal category airplanes that are approaching street address for the Docket Office
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![Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules 62033
We are issuing this rulemaking under (a) Comments Due Date 5.0, ‘‘Damage Tolerance Rating (DTR) System
the authority described in Subtitle VII, We must receive comments by October 24, Application,’’ of Boeing Document No. D6–
Part A, Subpart III, Section 44701: 2016. 35022, ‘‘Supplemental Structural Inspection
Document for Model 747 Airplanes,’’
‘‘General requirements.’’ Under that (b) Affected ADs Revision H, dated September 2013; and
section, Congress charges the FAA with Boeing Document No. D6–35022–1, ‘‘747–
This AD affects AD 2004–07–22 R1,
promoting safe flight of civil aircraft in Amendment 39–15326 (73 FR 1052, January 400 LCF Supplemental Structural Inspection
air commerce by prescribing regulations 7, 2008); corrected February 14, 2008 (73 FR Document—Appendix A,’’ dated November
for practices, methods, and procedures 8589) (‘‘AD 2004–07–22 R1’’). 2015; as applicable. Accomplishing the
the Administrator finds necessary for revision required by this paragraph
safety in air commerce. This regulation (c) Applicability terminates the actions required by paragraphs
is within the scope of that authority This AD applies to all The Boeing (f), (g), and (h) of AD 2004–07–22 R1. After
Company Model 747–100, 747–100B, 747– accomplishing the revision required by this
because it addresses an unsafe condition
100B SUD, 747–200B, 747–200C, 747–200F, paragraph, the revisions required by
that is likely to exist or develop on paragraphs (f), (g), and (h) of AD 2004–07–
747–300, 747–400, 747–400D, 747–400F,
products identified in this rulemaking 747SR, and 747SP series airplanes, 22 R1, as applicable, must be removed.
action. certificated in any category. (1) For all airplanes except Model 747–400
Note 1 to paragraph (c) of this AD: A LCF airplanes: SSIs listed in Boeing
Regulatory Findings
Model 747–400 LCF airplane is a Model 747– Document No. D6–35022, ‘‘Supplemental
We determined that this proposed AD 400 series airplane that has been modified Structural Inspection Document for Model
would not have federalism implications from a passenger airplane to a freighter 747 Airplanes,’’ Revision H, dated September
under Executive Order 13132. This configuration as specified in Boeing Service 2013.
proposed AD would not have a Bulletin 747–00–2084. (2) For Model 747–400 LCF airplanes: SSIs
listed in Boeing Document No. D6–35022,
substantial direct effect on the States, on (d) Subject ‘‘Supplemental Structural Inspection
the relationship between the national Document for Model 747 Airplanes,’’
Government and the States, or on the Air Transport Association (ATA) of
America Code 53, Fuselage; 54, Nacelles/ Revision H, dated September 2013; and SSIs
distribution of power and Pylons; 55, Stabilizers; 57, Wings. listed in Boeing Document No. D6–35022–1,
responsibilities among the various ‘‘747–400 LCF Supplemental Structural
levels of government. (e) Unsafe Condition Inspection Document—Appendix A,’’ dated
For the reasons discussed above, I This AD was prompted by a report of November 2015. For SSIs listed in both
certify this proposed regulation: incidents involving fatigue cracking in Boeing Document No. D6–35022–1, ‘‘747–
transport category airplanes that are 400 LCF Supplemental Structural Inspection
(1) Is not a ‘‘significant regulatory Document—Appendix A,’’ dated November
approaching or have exceeded their design
action’’ under Executive Order 12866, 2015; and Boeing Document No. D6–35022,
service objective and a structural
(2) Is not a ‘‘significant rule’’ under reevaluation by the manufacturer that ‘‘Supplemental Structural Inspection
the DOT Regulatory Policies and identified additional structural elements that Document for Model 747 Airplanes,’’
Procedures (44 FR 11034, February 26, qualify as structural significant items (SSIs). Revision H, dated September 2013:
1979), We are issuing this AD to ensure the Incorporate the SSIs listed Boeing Document
(3) Will not affect intrastate aviation continued structural integrity of all The No. D6–35022–1, ‘‘747–400 LCF
Boeing Company Model 747–100, 747–100B, Supplemental Structural Inspection
in Alaska, and Document—Appendix A,’’ dated November
747–100B SUD, 747–200B, 747–200C, 747–
(4) Will not have a significant 2015.
200F, 747–300, 747–400, 747–400D, 747–
economic impact, positive or negative, 400F, 747SR, and 747SP series airplanes.
on a substantial number of small entities (i) Inspection Compliance Times for All
(f) Compliance Model 747 Airplanes Except Model 747–400
under the criteria of the Regulatory
LCF airplanes
Flexibility Act. Comply with this AD within the
compliance times specified, unless already For all Model 747 airplanes except Model
List of Subjects in 14 CFR Part 39 done. 747–400 LCF airplanes: Perform inspections
to detect cracks of all structure identified in
Air transportation, Aircraft, Aviation (g) Definition of SSI Boeing Document No. D6–35022,
safety, Incorporation by reference, For the purposes of this AD, an SSI is ‘‘Supplemental Structural Inspection
Safety. defined as a principal structural element Document for Model 747 Airplanes,’’
The Proposed Amendment (PSE). A PSE is a structural element that Revision H, dated September 2013, at the
contributes significantly to the carrying of times specified in paragraph (i)(1), (i)(2), or
Accordingly, under the authority flight, ground, or pressurization loads, and (i)(3) of this AD, as applicable. Once the
delegated to me by the Administrator, whose integrity is essential in maintaining initial inspection has been performed, in
the FAA proposes to amend 14 CFR part the overall structural integrity of the airplane. order to remain in compliance with the
39 as follows: maintenance or inspection program, as
(h) Maintenance or Inspection Program required by paragraph (h) of this AD,
Revision for All Airplanes repetitive inspections are required at the
PART 39—AIRWORTHINESS
Prior to reaching the compliance intervals specified in Boeing Document No.
DIRECTIVES thresholds specified in paragraph (i)(1)(i), D6–35022, ‘‘Supplemental Structural
(i)(2)(i), (j)(1)(i), or (j)(2)(i) of this AD, as Inspection Document for Model 747
■ 1. The authority citation for part 39 applicable, or within 12 months after the Airplanes,’’ Revision H, dated September
continues to read as follows: effective date of this AD, whichever occurs 2013. Doing an inspection required by this
Authority: 49 U.S.C. 106(g), 40113, 44701. later: Incorporate a revision into the paragraph terminates the corresponding
mstockstill on DSK3G9T082PROD with PROPOSALS
maintenance or inspection program, as inspection required by paragraph (i) of AD
§ 39.13 [Amended] applicable, that provides no less than the 2004–07–22 R1.
■ 2. The FAA amends § 39.13 by adding required damage tolerance rating (DTR) for (1) For wing structure, except as provided
each SSI listed in the applicable service by paragraph (i)(3) of this AD: Inspect at the
the following new airworthiness
information specified in paragraph (h)(1) or times specified in paragraph (i)(1)(i) or
directive (AD): (h)(2) of this AD. The revision to the (i)(1)(ii) of this AD, whichever occurs later.
The Boeing Company: Docket No. FAA– maintenance or inspection program must (i) Within the applicable compliance time
2016–9067; Directorate Identifier 2016– include, and must be implemented in specified in paragraph (i)(1)(i)(A) or
NM–043–AD. accordance with, the procedures in Section (i)(1)(i)(B) of this AD.
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![Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules 62035
Issued in Renton, Washington, on August account.airworth-eas@airbus.com; A320, and A321 series airplanes. The
24, 2016. Internet: http://www.airbus.com. You MCAI states:
John P. Piccola, Jr., may view this referenced service During studies for a new landing gear
Acting Manager, Transport Airplane information at the FAA, Transport design, it was discovered that the single-
Directorate, Aircraft Certification Service. Airplane Directorate, 1601 Lind Avenue locked upper and lower cardan joints of the
[FR Doc. 2016–21147 Filed 9–7–16; 8:45 am] SW., Renton, WA. For information on MLG do not comply with the certification
BILLING CODE 4910–13–P the availability of this material at the specifications of (CS), (formerly Joint
FAA, call 425 227–1221. Aviation Requirements (JAR)) Part 25.607.
This condition, if not corrected, could lead
DEPARTMENT OF TRANSPORTATION Examining the AD Docket to MLG side stay locking failure that, during
take-off and landing, may result in damage to
You may examine the AD docket on
Federal Aviation Administration the aeroplane and detrimental effect on safe
the Internet at http:// flight.
www.regulations.gov by searching for To address this potential unsafe condition,
14 CFR Part 39 and locating Docket No. FAA–2016– the MLG manufacturer developed a
[Docket No. FAA–2016–9071; Directorate 9071; or in person at the Docket modification to change the single-locked
Identifier 2016–NM–019–AD] Management Facility between 9 a.m. MLG joint into a double-locked one. This
and 5 p.m., Monday through Friday, modification is available for in-service
RIN 2120–AA64 application through Messier-Bugatti-Dowty
except Federal holidays. The AD docket
contains this proposed AD, the (MBD) Service Bulletin (SB) 200–32–315 or
Airworthiness Directives; Airbus SB 201–32–63, or Airbus SB A320–32–1429.
Airplanes regulatory evaluation, any comments
For the reasons described above, this
received, and other information. The [EASA] AD requires modification or
AGENCY: Federal Aviation street address for the Docket Operations replacement of the MLG side stay assemblies
Administration (FAA), DOT. office (telephone: 800–647–5527) is in to introduce the double locking of the MLG
ACTION: Notice of proposed rulemaking the ADDRESSES section. Comments will upper and lower cardan joints.
(NPRM). be available in the AD docket shortly
after receipt. You may examine the MCAI in the
SUMMARY: We propose to adopt a new AD docket on the Internet at http://
FOR FURTHER INFORMATION CONTACT:
airworthiness directive (AD) for certain www.regulations.gov by searching for
Sanjay Ralhan, Aerospace Engineer,
Airbus Model A318, A319, A320, and and locating Docket No. FAA–2016–
International Branch, ANM–116,
A321 series airplanes. This proposed 9071.
Transport Airplane Directorate, FAA,
AD was prompted by an evaluation by 1601 Lind Avenue SW., Renton, WA Related Service Information Under 1
the design approval holder (DAH) 98057–3356; telephone: 425–227–1405; CFR Part 51
which indicates that the main landing fax: 425–227–1149.
gear (MLG) does not comply with We have reviewed the following
SUPPLEMENTARY INFORMATION:
certification specifications, which could service information. The service
result in a locking failure of the MLG Comments Invited information describes procedures for
side stay. This proposed AD would modifying the MLG side stay assembly.
We invite you to send any written
require modification or replacement of • Airbus Service Bulletin A320–32–
relevant data, views, or arguments about
certain MLG side stay assemblies. We 1429, dated September 10, 2015.
this proposed AD. Send your comments
are proposing this AD to prevent
possible collapse of the MLG during
to an address listed under the • Messier-Bugatti-Dowty Service
ADDRESSES section. Include ‘‘Docket No. Bulletin 200–32–315, dated April 24,
takeoff and landing.
FAA–2016–9071; Directorate Identifier 2015.
DATES: We must receive comments on 2016–NM–019–AD’’ at the beginning of
this proposed AD by October 24, 2016. • Messier-Bugatti-Dowty Service
your comments. We specifically invite
Bulletin 201–32–63, dated April 24,
ADDRESSES: You may send comments by comments on the overall regulatory,
2015.
any of the following methods: economic, environmental, and energy
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will This service information is reasonably
http://www.regulations.gov. Follow the consider all comments received by the available because the interested parties
instructions for submitting comments. closing date and may amend this have access to it through their normal
• Fax: 202–493–2251. proposed AD based on those comments. course of business or by the means
• Mail: U.S. Department of We will post all comments we identified in the ADDRESSES section.
Transportation, Docket Operations, M– receive, without change, to http:// FAA’s Determination and Requirements
30, West Building Ground Floor, Room www.regulations.gov, including any of This Proposed AD
W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
Washington, DC 20590. will also post a report summarizing each This product has been approved by
• Hand Delivery: U.S. Department of substantive verbal contact we receive the aviation authority of another
Transportation, Docket Operations, M– about this proposed AD. country, and is approved for operation
30, West Building Ground Floor, Room in the United States. Pursuant to our
W12–140, 1200 New Jersey Avenue SE., Discussion bilateral agreement with the State of
Washington, DC, between 9 a.m. and 5 The European Aviation Safety Agency Design Authority, we have been notified
mstockstill on DSK3G9T082PROD with PROPOSALS
p.m., Monday through Friday, except (EASA), which is the Technical Agent of the unsafe condition described in the
Federal holidays. for the Member States of the European MCAI and service information
For service information identified in Union, has issued EASA AD 2016–0018, referenced above. We are proposing this
this NPRM, contact Airbus, dated January 19, 2016 (referred to after AD because we evaluated all pertinent
Airworthiness Office—EIAS, 1 Rond this as the Mandatory Continuing information and determined an unsafe
Point Maurice Bellonte, 31707 Blagnac Airworthiness Information, or ‘‘the condition exists and is likely to exist or
Cedex, France; telephone: +33 5 61 93 MCAI’’), to correct an unsafe condition develop on other products of the same
36 96; fax: +33 5 61 93 44 51; email: for certain Airbus Model A318, A319, type design.
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Document Created: 2018-02-09 13:12:28
Document Modified: 2018-02-09 13:12:28
| 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 October 24, 2016. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 62031 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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