83 FR 38091 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 150 (August 3, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 150 (August 3, 2018)
| Page Range | 38091-38096 | |
| FR Document | 2018-16497 |
[Federal Register Volume 83, Number 150 (Friday, August 3, 2018)] [Proposed Rules] [Pages 38091-38096] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-16497] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0641; Product Identifier 2018-NM-032-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2017-22- 07, which applies to certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017- 22-07 requires repetitive inspections of the frame forks, and corrective actions if necessary. AD 2017-22-07 also includes optional modifications that constitute terminating action. Since we issued AD 2017-22-07, an evaluation was done by the design approval holder (DAH) indicating that the frame forks and outer skin on the forward and aft cargo compartment doors are subject to widespread fatigue damage (WFD), and a determination was made that a modification of the frame forks must be accomplished. This proposed AD would require modifying certain forward and aft cargo compartment doors, and related investigative and corrective actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 17, 2018. 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 Airbus, Airworthiness Office--EIAS, 2 Rond Point Emile Dewoitine, 31700 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. Examining the AD Docket You may examine the AD docket on the internet at http:// [[Page 38092]] www.regulations.gov by searching for and locating Docket No. FAA-2018- 0641; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223. 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-2018-0641; Product Identifier 2018-NM-032-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 based on 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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread 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. This condition is known as WFD. It is associated with general degradation of large areas of structure with similar structural details and stress levels. 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. We issued AD 2017-22-07, Amendment 39-19087 (82 FR 56158, November 28, 2017) (``AD 2017-22-07''), for certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017-22-07 requires repetitive inspections of the frame forks, and corrective actions if necessary. AD 2017-22-07 also includes optional modifications that constitute terminating action. AD 2017-22- 07 resulted from a report of cracks on frame forks and outer skin on the forward and aft cargo compartment doors. We issued AD 2017-22-07 to address cracks on the frame forks and outer skin on the forward and aft cargo compartment doors, which could lead to reduced structural integrity and failure of the cargo compartment door, possible decompression of the airplane, and injury to occupants. Actions Since AD 2017-22-07 Was Issued Since we issued AD 2017-22-07, an evaluation was done by the DAH indicating that the frame forks and outer skin on the forward and aft cargo compartment doors are subject to WFD, and a determination was made that a modification of the frame forks must be accomplished. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2018-0024, dated January 29, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, - 231, and -232 airplanes. The MCAI states: During full scale fatigue test, cracks were found on frame forks and outer skin on forward and aft cargo doors. To improve the fatigue behaviour of the frame forks, Airbus introduced modification (mod) 22948 in production, and issued inspection Service Bulletin (SB) A320-52-1032 and mod SB A320-52-1042, both recommended. Since those actions were taken, further improved cargo compartment doors were introduced in production through Airbus mod 26213, on aeroplanes having [manufacturer serial number] MSN 0759 and up. In the frame of the Widespread Fatigue Damage (WFD) study, it was determined that repetitive inspection are necessary for aft and forward cargo compartment doors on aeroplanes that are in pre-mod 26213 configuration. Failure to detect cracks would reduce the cargo door structural integrity. This condition, if not detected and corrected, could lead to cargo door failure, possibly resulting in decompression of the aeroplane and injury to occupants. To address this unsafe condition, Airbus issued SB A320-52-1171 to provide instructions for repetitive special detailed inspections (SDI). This SB was later revised to correct the list of affected cargo doors. Airbus also issued SB A320-52-1170, introducing a door modification which would allow terminating the repetitive SDI[s]. Consequently, EASA issued AD 2016-0187 [which corresponds to FAA AD 2017-22-07] to require repetitive SDI[s] of the affected cargo doors and, depending on findings, the accomplishment of applicable repairs. That [EASA] AD also included reference to SB A320-52-1170 as optional terminating action. Since that [EASA] AD was issued, further investigations linked to the WFD analysis highlighted that, to meet the WFD requirements, it is necessary to require [[Page 38093]] embodiment of the terminating action modification. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2016-0187, which is superseded, and requires modification of all affected cargo doors, which constitutes terminating action for the repetitive SDI[s] required by this [EASA] AD. The related investigative action is a high frequency eddy current (HFEC) rotating probe inspection for cracks. Corrective actions include, among other things, oversizing and cold-expanding any affected holes and repair. You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0641. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, which describes procedures for repetitive special detailed inspections of all frame forks in the beam 4 area of any affected door, and corrective actions. Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997, which describes procedures for modification of all affected forward and aft cargo compartment doors. Service Bulletin A320-52-1170, including Appendices 01 and 02, dated September 5, 2016, which describes procedures for modifying all affected forward and aft cargo compartment doors, including oversize and cold working of riveting for all frame forks. 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 and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Explanation of Compliance Time The compliance time for the replacement 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. Paragraphs (j)(2) and (j)(3) of AD 2017-22-07 allowed an optional terminating modification that could be done at any time. This proposed AD would still permit that optional terminating modification, but with new limitations on the compliance time, i.e., the optional modification must be done on or after the accumulation of 21,700 flight cycles since first installation of the door on an airplane in order to terminate the repetitive inspections. The repetitive inspections are not terminated if the modification is done before the accumulation of 21,700 flight cycles since first installation of the door on an airplane. These limitations match those in EASA AD 2018-0024, dated January 29, 2018. Costs of Compliance We estimate that this proposed AD affects 88 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Modification.................... 24 work-hours x Up to $240........ Up to $2,280...... Up to $200,640. $85 per hour = $2,040. Inspection...................... 25 work-hours x $0................ $2,125............ $187,000. $85 per hour = $2,125. ---------------------------------------------------------------------------------------------------------------- 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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. [[Page 38094]] The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2017-22-07, Amendment 39-19087 (82 FR 56158, November 28, 2017), and adding the following new AD: Airbus: Docket No. FAA-2018-0641; Product Identifier 2018-NM-032-AD. (a) Comments Due Date We must receive comments by September 17, 2018. (b) Affected ADs This AD replaces AD 2017-22-07, Amendment 39-19087 (82 FR 56158, November 28, 2017) (``AD 2017-22-07''). (c) Applicability This AD applies to Airbus Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, - 216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category, manufacturer serial numbers through 0758 inclusive. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the frame forks and outer skin on the forward and aft cargo compartment doors are subject to widespread fatigue damage (WFD), and a determination that a modification of the frame forks must be accomplished. We are issuing this AD to address cracks on the frame forks and outer skin on the forward and aft cargo compartment doors, which could lead to reduced structural integrity and failure of the cargo compartment door, possible decompression of the airplane, and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Definition of Affected Door, With No Changes This paragraph restates the definition in paragraph (g) of AD 2017-22-07, with no changes. For the purpose of this AD, an ``affected door'' is a forward or aft cargo compartment door, having any part number listed in table 1 to paragraph (g) of this AD, except a cargo compartment door on which Airbus Service Bulletin A320-52-1042 or Airbus Service Bulletin A320-52-1170 is embodied. [GRAPHIC] [TIFF OMITTED] TP03AU18.000 (h) Retained Repetitive Special Detailed Inspection of Frame Forks, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2017-22-07, with no changes. At the latest of the compliance times listed in paragraphs (h)(1) through (h)(4) of this AD: Do a special detailed inspection of all frame forks in the beam 4 area of any affected door as defined in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, except as specified in paragraphs (l) and (m) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. A review of the airplane delivery or maintenance records is acceptable to identify any affected door installed on the airplane, provided that the cargo compartment door part number can be conclusively determined from that review. (1) Before exceeding 37,500 flight cycles since first installation of the door on an airplane. (2) Within 900 flight cycles after January 2, 2018 (the effective date of AD 2017-22-07), without exceeding 41,950 flight cycles since first installation of the door on an airplane. (3) Within 50 flight cycles after January 2, 2018 (the effective date of AD 2017-22-07), for a door having reached or exceeded 41,900 flight cycles since first installation on an airplane. [[Page 38095]] (4) Within 3,000 flight cycles since the last inspection of the door as specified in Airbus Service Bulletin A320-52-1032. (i) Retained Corrective Actions, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2017-22-07, with no changes. If any crack is found during any inspection required by paragraph (h) of this AD, before further flight, do all applicable corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, except as specified in paragraphs (l) and (m) of this AD. Accomplishment of applicable corrective actions does not constitute terminating action for the repetitive inspections. (j) Terminating Modification Before the accumulation of 56,300 total flight cycles, but not before the accumulation of 21,700 total flight cycles since first installation of the affected door on an airplane: Modify all affected doors of an airplane, including accomplishment of all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1170, including Appendices 01 and 02, dated September 5, 2016. Accomplishing this modification constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (k) Retained Optional Terminating Action, With Changes Related to Compliance This paragraph restates the requirements of paragraph (j) of AD 2017-22-07, with changes related to compliance. (1) Modification of all affected doors of an airplane before the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph (j) of this AD, for that airplane, provided that, after modification, no affected door is re-installed on that airplane. On or after the effective date of this AD, the modification required by paragraph (j) of this AD must be done. (2) Modification of all affected doors of an airplane including accomplishment of all applicable related investigative and corrective actions, if done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1170, dated September 5, 2016, except as specified in paragraph (l) of this AD, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph (j) of this AD, for that airplane, provided that, after modification, no affected door is re-installed on that airplane. On or after the effective date of this AD, the modification required by paragraph (j) of this AD must be done. (3) Modification of all affected doors on an airplane, in case of finding damaged frame forks, as specified in an Airbus Repair Design Approval Sheet (RDAS), if done before the effective date of this AD and done in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); constitutes terminating action for the repetitive inspection specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph (j) of this AD, for that airplane, provided that, after modification, no affected door is re-installed on that airplane. On or after the effective date of this AD, the modification required by paragraph (j) of this AD must be done. (l) Retained Exception to Service Information This paragraph restates the requirements of paragraph (k) of AD 2017-22-07, with no changes. Where Airbus Service Bulletin A320-52- 1170, including Appendices 01 and 02, dated September 5, 2016; or Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017; specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (p)(2) of this AD. (m) Retained No Reporting Requirement This paragraph restates the requirements of paragraph (l) of AD 2017-22-07, with no changes. Although Airbus Service Bulletin A320- 52-1171, Revision 02, dated April 10, 2017, specifies to submit certain information to the manufacturer, and specifies that action as ``RC,'' this AD does not include that requirement. (n) Retained Credit for Previous Actions This paragraph restates the requirements of paragraph (m) of AD 2017-22-07, with no changes. (1) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before January 2, 2018 (the effective date of AD 2017-22-07), using Airbus Service Bulletin A320-52-1171, dated October 29, 2015, provided that it can be conclusively determined that any part number D52371000018 was also inspected as specified in paragraph (h) of this AD. (2) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before January 2, 2018 (the effective date of AD 2017-22-07), using Airbus Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016. (o) Parts Installation Limitation As of the effective date of this AD, no person may install, on any airplane, an affected door specified in paragraph (g) of this AD, unless less than 56,300 flight cycles have accumulated since first installation of the door on an airplane, and unless the door has been inspected in accordance with the requirements of paragraph (h) of this AD and all applicable corrective actions have been done in accordance with paragraph (i) of this AD. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 International Section, send it to the attention of the person identified in paragraph (p)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): Except as specified in paragraphs (l) and (m) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2018-0024, dated January 29, 2018, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0641. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 2 Rond Point Emile Dewoitine, 31700 Blagnac Cedex, France; telephone: +33 [[Page 38096]] 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; internet: http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. Issued in Des Moines, Washington, on July 24, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-16497 Filed 8-2-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 150 / Friday, August 3, 2018 / Proposed Rules 38091
applicable service information specified in Transport Standards Branch, FAA; or the Notice of proposed rulemaking
ACTION:
paragraphs (i)(1) through (i)(7) of this AD. European Aviation Safety Agency (EASA); or (NPRM).
(1) Airbus Service Bulletin A330–29–3131, Airbus SAS’s EASA Design Organization
dated August 11, 2017. Approval (DOA). If approved by the DOA, SUMMARY: We propose to supersede
(2) Airbus Service Bulletin A330–29–3132, the approval must include the DOA- Airworthiness Directive (AD) 2017–22–
dated August 11, 2017. authorized signature. 07, which applies to certain Airbus
(3) Airbus Service Bulletin A330–29–3133, (3) Required for Compliance (RC): If any Model A319 series airplanes; Model
dated August 11, 2017. service information contains procedures or A320–211, –212, –214, –231, –232, and
(4) Airbus Service Bulletin A340–29–4099, tests that are identified as RC, those
dated August 11. 2017. procedures and tests must be done to comply
–233 airplanes; and Model A321–111,
(5) Airbus Service Bulletin A340–29–4100, with this AD; any procedures or tests that are –112, –131, –211, –212, –213, –231, and
dated August 11, 2017. not identified as RC are recommended. Those –232 airplanes. AD 2017–22–07 requires
(6) Airbus Service Bulletin A340–29–4101, procedures and tests that are not identified repetitive inspections of the frame forks,
dated August 11, 2017. as RC may be deviated from using accepted and corrective actions if necessary. AD
(7) Airbus Service Bulletin A340–29–5026, methods in accordance with the operator’s 2017–22–07 also includes optional
dated August 11, 2017. maintenance or inspection program without modifications that constitute
obtaining approval of an AMOC, provided terminating action. Since we issued AD
(j) Part Re-identification
the procedures and tests identified as RC can 2017–22–07, an evaluation was done by
(1) For Group 1 airplanes: Concurrently be done and the airplane can be put back in
with the PRV replacement required by
the design approval holder (DAH)
an airworthy condition. Any substitutions or
paragraph (i) of this AD, re-identify the part changes to procedures or tests identified as
indicating that the frame forks and outer
numbers of affected HRs as specified in table RC require approval of an AMOC. skin on the forward and aft cargo
1 to paragraphs (g), (h), (i), and (j) of this AD, compartment doors are subject to
in accordance with the applicable service (n) Related Information widespread fatigue damage (WFD), and
information specified in paragraphs (i)(1) (1) Refer to Mandatory Continuing a determination was made that a
through (i)(7) of this AD. Airworthiness Information (MCAI) EASA AD modification of the frame forks must be
(2) For Group 2 airplanes: At the applicable 2018–0064, dated March 23, 2018, for related accomplished. This proposed AD would
time specified in table 1 to paragraphs (g), information. This MCAI may be found in the require modifying certain forward and
(h), (i), and (j) of this AD, re-identify the part AD docket on the internet at http:// aft cargo compartment doors, and
numbers of affected PRVs and HRs, in www.regulations.gov by searching for and
accordance with the applicable service locating Docket No. FAA–2018–0704.
related investigative and corrective
information specified in paragraphs (i)(1) (2) For more information about this AD, actions. We are proposing this AD to
through (i)(7) of this AD. contact Vladimir Ulyanov, Aerospace address the unsafe condition on these
Engineer, International Section, Transport products.
(k) Terminating Action
Standards Branch, FAA, 2200 South 216th DATES: We must receive comments on
Replacement of all affected PRVs on an St., Des Moines, WA 98198; telephone and
airplane, as required by paragraph (i) of this
this proposed AD by September 17,
fax: 206–231–3229.
AD, terminates all requirements of AD 2017– 2018.
(3) For service information identified in
01–08 for that airplane. this AD, contact Airbus SAS, Airworthiness ADDRESSES: You may send comments,
(l) Parts Installation Prohibition Office—EAL, Rond Point Emile Dewoitine using the procedures found in 14 CFR
No: 2, 31700 Blagnac Cedex, France; 11.43 and 11.45, by any of the following
(1) For Group 1 airplanes: After telephone: +33 5 61 93 36 96; fax: +33 5 61 methods:
replacement of all affected parts as required
by paragraph (i) of this AD, do not install any
93 45 80; email: airworthiness.A330-A340@ • Federal eRulemaking Portal: Go to
airbus.com; internet http://www.airbus.com. http://www.regulations.gov. Follow the
affected PRV. You may view this service information at the
(2) For Group 2 airplanes: As of the instructions for submitting comments.
FAA, Transport Standards Branch, 2200
effective date of this AD, do not install any South 216th St., Des Moines, WA. For
• Fax: 202–493–2251.
affected PRV. information on the availability of this
• Mail: U.S. Department of
material at the FAA, call 206–231–3195. Transportation, Docket Operations, M–
(m) Other FAA AD Provisions 30, West Building Ground Floor, Room
The following provisions also apply to this Issued in Des Moines, Washington, on July W12–140, 1200 New Jersey Avenue SE,
AD: 25, 2018. Washington, DC 20590.
(1) Alternative Methods of Compliance James Cashdollar, • Hand Delivery: Deliver to Mail
(AMOCs): The Manager, International address above between 9 a.m. and 5
Acting Director, System Oversight Division,
Section, Transport Standards Branch, FAA, p.m., Monday through Friday, except
Aircraft Certification Service.
has the authority to approve AMOCs for this Federal holidays.
AD, if requested using the procedures found [FR Doc. 2018–16574 Filed 8–2–18; 8:45 am]
For service information identified in
in 14 CFR 39.19. In accordance with 14 CFR BILLING CODE 4910–13–P
this NPRM, contact Airbus,
39.19, send your request to your principal
inspector or local Flight Standards District Airworthiness Office—EIAS, 2 Rond
Office, as appropriate. If sending information DEPARTMENT OF TRANSPORTATION Point Emile Dewoitine, 31700 Blagnac
directly to the International Branch, send it Cedex, France; telephone: +33 5 61 93
to the attention of the person identified in Federal Aviation Administration 36 96; fax: +33 5 61 93 44 51; email:
paragraph (n)(2) of this AD. Information may account.airworth-eas@airbus.com;
be emailed to: 9-ANM-116-AMOC- 14 CFR Part 39 internet: http://www.airbus.com. You
REQUESTS@faa.gov. Before using any may view this referenced service
approved AMOC, notify your appropriate [Docket No. FAA–2018–0641; Product information at the FAA, Transport
amozie on DSK3GDR082PROD with PROPOSALS1
principal inspector, or lacking a principal Identifier 2018–NM–032–AD] Standards Branch, 2200 South 216th St.,
inspector, the manager of the local flight
standards district office/certificate holding RIN 2120–AA64
Des Moines, WA. For information on the
district office. availability of this material at the FAA,
(2) Contacting the Manufacturer: For any Airworthiness Directives; Airbus call 206–231–3195.
requirement in this AD to obtain corrective Airplanes Examining the AD Docket
actions from a manufacturer, the action must
be accomplished using a method approved AGENCY:Federal Aviation You may examine the AD docket on
by the Manager, International Section, Administration (FAA), DOT. the internet at http://
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![38092 Federal Register / Vol. 83, No. 150 / Friday, August 3, 2018 / Proposed Rules
www.regulations.gov by searching for is operated long enough without any decompression of the airplane, and
and locating Docket No. FAA–2018– intervention. injury to occupants.
0641; or in person at the Docket The FAA’s WFD final rule (75 FR Actions Since AD 2017–22–07 Was
Management Facility between 9 a.m. 69746, November 15, 2010) became Issued
and 5 p.m., Monday through Friday, effective on January 14, 2011. The WFD
except Federal holidays. The AD docket rule requires certain actions to prevent Since we issued AD 2017–22–07, an
contains this NPRM, the regulatory structural failure due to WFD evaluation was done by the DAH
evaluation, any comments received, and throughout the operational life of indicating that the frame forks and outer
other information. The street address for certain existing transport category skin on the forward and aft cargo
the Docket Operations office (telephone airplanes and all of these airplanes that compartment doors are subject to WFD,
800–647–5527) is in the ADDRESSES will be certificated in the future. For and a determination was made that a
section. Comments will be available in existing and future airplanes subject to modification of the frame forks must be
the AD docket shortly after receipt. the WFD rule, the rule requires that accomplished.
DAHs establish a limit of validity (LOV) The European Aviation Safety Agency
FOR FURTHER INFORMATION CONTACT:
of the engineering data that support the (EASA), which is the Technical Agent
Sanjay Ralhan, Aerospace Engineer,
structural maintenance program. for the Member States of the European
International Section, Transport
Operators affected by the WFD rule may Union, has issued EASA Airworthiness
Standards Branch, FAA, 2200 South
not fly an airplane beyond its LOV, Directive 2018–0024, dated January 29,
216th St., Des Moines, WA 98198;
unless an extended LOV is approved. 2018 (referred to after this as the
telephone and fax 206–231–3223.
The WFD rule (75 FR 69746, Mandatory Continuing Airworthiness
SUPPLEMENTARY INFORMATION: Information, or ‘‘the MCAI’’), to correct
November 15, 2010) does not require
Comments Invited identifying and developing maintenance an unsafe condition for certain Airbus
actions if the DAHs can show that such Model A319 series airplanes; Model
We invite you to send any written A320–211, –212, –214, –216, –231,
relevant data, views, or arguments about actions are not necessary to prevent
WFD before the airplane reaches the –232, and –233 airplanes; and Model
this proposal. Send your comments to A321–111, –112, –131, –211, –212,
an address listed under the ADDRESSES LOV. Many LOVs, however, do depend
on accomplishment of future –213, –231, and –232 airplanes. The
section. Include ‘‘Docket No. FAA– MCAI states:
2018–0641; Product Identifier 2018– maintenance actions. As stated in the
NM–032–AD’’ at the beginning of your WFD rule, any maintenance actions During full scale fatigue test, cracks were
comments. We specifically invite necessary to reach the LOV will be found on frame forks and outer skin on
mandated by airworthiness directives forward and aft cargo doors. To improve the
comments on the overall regulatory, fatigue behaviour of the frame forks, Airbus
economic, environmental, and energy through separate rulemaking actions.
introduced modification (mod) 22948 in
aspects of this proposed AD. We will In the context of WFD, this action is production, and issued inspection Service
consider all comments received by the necessary to enable DAHs to propose Bulletin (SB) A320–52–1032 and mod SB
closing date and may amend this LOVs that allow operators the longest A320–52–1042, both recommended. Since
proposed AD based on those comments. operational lives for their airplanes, and those actions were taken, further improved
We will post all comments we still ensure that WFD will not occur. cargo compartment doors were introduced in
receive, without change, to http:// This approach allows for an production through Airbus mod 26213, on
implementation strategy that provides aeroplanes having [manufacturer serial
www.regulations.gov, including any number] MSN 0759 and up.
personal information you provide. We flexibility to DAHs in determining the In the frame of the Widespread Fatigue
will also post a report summarizing each timing of service information Damage (WFD) study, it was determined that
substantive verbal contact we receive development (with FAA approval), repetitive inspection are necessary for aft and
about this proposed AD. while providing operators with certainty forward cargo compartment doors on
regarding the LOV applicable to their aeroplanes that are in pre-mod 26213
Discussion airplanes. configuration. Failure to detect cracks would
Fatigue damage can occur locally, in We issued AD 2017–22–07, reduce the cargo door structural integrity.
small areas or structural design details, Amendment 39–19087 (82 FR 56158, This condition, if not detected and
corrected, could lead to cargo door failure,
or globally, in widespread areas. November 28, 2017) (‘‘AD 2017–22– possibly resulting in decompression of the
Multiple-site damage is widespread 07’’), for certain Airbus Model A319 aeroplane and injury to occupants.
damage that occurs in a large structural series airplanes; Model A320–211, –212, To address this unsafe condition, Airbus
element such as a single rivet line of a –214, –231, –232, and –233 airplanes; issued SB A320–52–1171 to provide
lap splice joining two large skin panels. and Model A321–111, –112, –131, –211, instructions for repetitive special detailed
Widespread damage can also occur in –212, –213, –231, and –232 airplanes. inspections (SDI). This SB was later revised
multiple elements such as adjacent AD 2017–22–07 requires repetitive to correct the list of affected cargo doors.
frames or stringers. Multiple-site inspections of the frame forks, and Airbus also issued SB A320–52–1170,
introducing a door modification which
damage and multiple-element damage corrective actions if necessary. AD would allow terminating the repetitive
cracks are typically too small initially to 2017–22–07 also includes optional SDI[s].
be reliably detected with normal modifications that constitute Consequently, EASA issued AD 2016–0187
inspection methods. Without terminating action. AD 2017–22–07 [which corresponds to FAA AD 2017–22–07]
intervention, these cracks will grow, resulted from a report of cracks on frame to require repetitive SDI[s] of the affected
amozie on DSK3GDR082PROD with PROPOSALS1
and eventually compromise the forks and outer skin on the forward and cargo doors and, depending on findings, the
structural integrity of the airplane. This aft cargo compartment doors. We issued accomplishment of applicable repairs. That
condition is known as WFD. It is AD 2017–22–07 to address cracks on the [EASA] AD also included reference to SB
A320–52–1170 as optional terminating
associated with general degradation of frame forks and outer skin on the action.
large areas of structure with similar forward and aft cargo compartment Since that [EASA] AD was issued, further
structural details and stress levels. As doors, which could lead to reduced investigations linked to the WFD analysis
an airplane ages, WFD will likely occur, structural integrity and failure of the highlighted that, to meet the WFD
and will certainly occur if the airplane cargo compartment door, possible requirements, it is necessary to require
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![Federal Register / Vol. 83, No. 150 / Friday, August 3, 2018 / Proposed Rules 38093
embodiment of the terminating action • Service Bulletin A320–52–1170, replaced before WFD develops in
modification. including Appendices 01 and 02, dated airplanes. Standard inspection
For the reason described above, this September 5, 2016, which describes techniques cannot be relied on to detect
[EASA] AD retains the requirements of EASA
procedures for modifying all affected WFD before it becomes a hazard to
AD 2016–0187, which is superseded, and
requires modification of all affected cargo forward and aft cargo compartment flight. We will not grant any extensions
doors, which constitutes terminating action doors, including oversize and cold of the compliance time to complete any
for the repetitive SDI[s] required by this working of riveting for all frame forks. AD-mandated service bulletin related to
[EASA] AD. This service information is reasonably WFD without extensive new data that
The related investigative action is a available because the interested parties would substantiate and clearly warrant
high frequency eddy current (HFEC) have access to it through their normal such an extension.
rotating probe inspection for cracks. course of business or by the means Paragraphs (j)(2) and (j)(3) of AD
Corrective actions include, among other identified in the ADDRESSES section. 2017–22–07 allowed an optional
things, oversizing and cold-expanding terminating modification that could be
FAA’s Determination and Requirements
any affected holes and repair. You may done at any time. This proposed AD
of This Proposed AD
examine the MCAI in the AD docket on would still permit that optional
the internet at http:// This product has been approved by terminating modification, but with new
www.regulations.gov by searching for the aviation authority of another limitations on the compliance time, i.e.,
and locating Docket No. FAA–2018– country, and is approved for operation the optional modification must be done
0641. in the United States. Pursuant to our on or after the accumulation of 21,700
bilateral agreement with the State of flight cycles since first installation of
Related Service Information Under 1 Design Authority, we have been notified the door on an airplane in order to
CFR Part 51 of the unsafe condition described in the terminate the repetitive inspections. The
Airbus has issued the following MCAI and service information repetitive inspections are not terminated
service information. referenced above. We are proposing this if the modification is done before the
• Service Bulletin A320–52–1171, AD because we evaluated all pertinent accumulation of 21,700 flight cycles
Revision 02, dated April 10, 2017, information and determined an unsafe since first installation of the door on an
which describes procedures for condition exists and is likely to exist or airplane. These limitations match those
repetitive special detailed inspections of develop on other products of these same in EASA AD 2018–0024, dated January
all frame forks in the beam 4 area of any type designs. 29, 2018.
affected door, and corrective actions. Explanation of Compliance Time Costs of Compliance
• Service Bulletin A320–52–1042,
Revision 2, dated January 14, 1997, The compliance time for the We estimate that this proposed AD
which describes procedures for replacement specified in this proposed affects 88 airplanes of U.S. registry.
modification of all affected forward and AD for addressing WFD was established We estimate the following costs to
aft cargo compartment doors. to ensure that discrepant structure is comply with this proposed AD:
Cost on
Action Labor cost Parts cost Cost per product U.S. operators
Modification ....................... 24 work-hours × $85 per Up to $240 ........................ Up to $2,280 ..................... Up to $200,640.
hour = $2,040.
Inspection .......................... 25 work-hours × $85 per $0 ...................................... $2,125 ............................... $187,000.
hour = $2,125.
Authority for This Rulemaking products identified in this rulemaking distribution of power and
action. responsibilities among the various
Title 49 of the United States Code This proposed AD is issued in levels of government.
specifies the FAA’s authority to issue accordance with authority delegated by For the reasons discussed above, I
rules on aviation safety. Subtitle I, the Executive Director, Aircraft certify this proposed regulation:
section 106, describes the authority of Certification Service, as authorized by
the FAA Administrator. FAA Order 8000.51C. In accordance 1. Is not a ‘‘significant regulatory
with that order, issuance of ADs is action’’ under Executive Order 12866,
Subtitle VII: Aviation Programs,
describes in more detail the scope of the normally a function of the Compliance 2. Is not a ‘‘significant rule’’ under the
Agency’s authority. and Airworthiness Division, but during DOT Regulatory Policies and Procedures
this transition period, the Executive (44 FR 11034, February 26, 1979),
We are issuing this rulemaking under Director has delegated the authority to
the authority described in Subtitle VII, 3. Will not affect intrastate aviation in
issue ADs applicable to transport Alaska, and
Part A, Subpart III, Section 44701: category airplanes to the Director of the
‘‘General requirements.’’ Under that System Oversight Division. 4. Will not have a significant
section, Congress charges the FAA with economic impact, positive or negative,
amozie on DSK3GDR082PROD with PROPOSALS1
promoting safe flight of civil aircraft in Regulatory Findings on a substantial number of small entities
air commerce by prescribing regulations We determined that this proposed AD under the criteria of the Regulatory
for practices, methods, and procedures would not have federalism implications Flexibility Act.
the Administrator finds necessary for under Executive Order 13132. This List of Subjects in 14 CFR Part 39
safety in air commerce. This regulation proposed AD would not have a
is within the scope of that authority substantial direct effect on the States, on Air transportation, Aircraft, Aviation
because it addresses an unsafe condition the relationship between the national safety, Incorporation by reference,
that is likely to exist or develop on Government and the States, or on the Safety.
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![38096 Federal Register / Vol. 83, No. 150 / Friday, August 3, 2018 / Proposed Rules
5 61 93 36 96; fax: +33 5 61 93 44 51; email: p.m., Monday through Friday, except Discussion
account.airworth-eas@airbus.com; internet: Federal holidays.
http://www.airbus.com. You may view this We have received reports of damaged
For service information identified in vapor seals, block seals, and heat shield
service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des this NPRM, contact Boeing Commercial seals on the outboard pylons between
Moines, WA. For information on the Airplanes, Attention: Contractual & Data the engine strut and aft fairing. Such
availability of this material at the FAA, call Services (C&DS), 2600 Westminster damage could allow flammable fluid
206–231–3195. Blvd., MC 110–SK57, Seal Beach, CA leakage out of the aft fairing. This
90740–5600; telephone 562–797–1717; condition, if not addressed, could result
Issued in Des Moines, Washington, on July internet https:// in an uncontrolled fire in the engine
24, 2018. www.myboeingfleet.com. You may view strut.
James Cashdollar, this referenced service information at
the FAA, Transport Standards Branch, Related Service Information Under 1
Acting Director, System Oversight Division,
Aircraft Certification Service. 2200 South 216th St., Des Moines, WA. CFR Part 51
[FR Doc. 2018–16497 Filed 8–2–18; 8:45 am] For information on the availability of We reviewed Boeing Alert Service
BILLING CODE 4910–13–P this material at the FAA, call 206–231– Bulletin 747–54A2247, dated August 3,
3195. It is also available on the internet 2017. This service information describes
at http://www.regulations.gov by procedures for installing new aft fairing
DEPARTMENT OF TRANSPORTATION searching for and locating Docket No. vapor seals, heatshield seals, heatshield
FAA–2018–0703. seal retainers, block seals, and outboard
Federal Aviation Administration lateral restraint access panels. This
Examining the AD Docket service information is reasonably
14 CFR Part 39 You may examine the AD docket on available because the interested parties
the internet at http:// have access to it through their normal
[Docket No. FAA–2018–0703; Product course of business or by the means
Identifier 2018–NM–007–AD] www.regulations.gov by searching for
and locating Docket No. FAA–2018– identified in the ADDRESSES section.
RIN 2120–AA64 0703; or in person at the Docket FAA’s Determination
Management Facility between 9 a.m.
Airworthiness Directives; The Boeing We are proposing this AD because we
and 5 p.m., Monday through Friday,
Company Airplanes evaluated all the relevant information
except Federal holidays. The AD docket
and determined the unsafe condition
contains this NPRM, the regulatory
AGENCY: Federal Aviation described previously is likely to exist or
evaluation, any comments received, and
Administration (FAA), DOT. develop in other products of the same
other information. The street address for
ACTION: Notice of proposed rulemaking type design.
the Docket Office (phone: 800–647–
(NPRM). 5527) is in the ADDRESSES section. Proposed AD Requirements
SUMMARY: We propose to adopt a new Comments will be available in the AD This proposed AD would require
airworthiness directive (AD) for all The docket shortly after receipt. accomplishment of the actions
Boeing Company Model 747–8 and 747– FOR FURTHER INFORMATION CONTACT: identified as ‘‘RC’’ (required for
8F series airplanes. This proposed AD Christopher Baker, Aerospace Engineer, compliance) in the Accomplishment
was prompted by reports of damaged Propulsion Section, FAA, Seattle ACO Instructions of Boeing Alert Service
vapor seals, block seals, and heat shield Branch, 2200 South 216th St., Des Bulletin 747–54A2247, dated August 3,
seals on the outboard pylons between Moines, WA 98198; phone and fax: 206– 2017, described previously, except as
the engine strut and aft fairing. This 231–3552; email: Christopher.R.Baker@ discussed under ‘‘Differences Between
proposed AD would require installing faa.gov. this Proposed AD and the Service
new aft fairing vapor seals, heatshield Information,’’ and except for any
SUPPLEMENTARY INFORMATION:
seals, heatshield seal retainers, block differences identified as exceptions in
seals and outboard lateral restraint Comments Invited the regulatory text of this proposed AD.
access panels. We are proposing this AD For information on the procedures
We invite you to send any written and compliance times, see this service
to address the unsafe condition on these
relevant data, views, or arguments about information at http://
products.
this proposal. Send your comments to www.regulations.gov by searching for
DATES: We must receive comments on an address listed under the ADDRESSES
this proposed AD by September 17, and locating Docket No. FAA–2018–
section. Include ‘‘Docket No. FAA– 0703.
2018. 2018–0703; Product Identifier 2018–
ADDRESSES: You may send comments, NM–007–AD’’ at the beginning of your Differences Between This Proposed AD
using the procedures found in 14 CFR comments. We specifically invite and the Service Information
11.43 and 11.45, by any of the following comments on the overall regulatory, The applicability in this proposed AD
methods: economic, environmental, and energy does not refer to paragraph 1.A.,
• Federal eRulemaking Portal: Go to aspects of this NPRM. We will consider ‘‘Effectivity,’’ of Boeing Alert Service
http://www.regulations.gov. Follow the all comments received by the closing Bulletin 747–54A2247, dated August 3,
instructions for submitting comments. date and may amend this NPRM 2017. The service information does not
amozie on DSK3GDR082PROD with PROPOSALS1
• Fax: 202–493–2251. because of those comments. contain a comprehensive list of the
• Mail: U.S. Department of We will post all comments we airplanes affected by the identified
Transportation, Docket Operations, M– receive, without change, to http:// unsafe condition because the spare parts
30, West Building Ground Floor, Room www.regulations.gov, including any identified in paragraph (j) of this AD
W12–140, 1200 New Jersey Avenue SE, personal information you provide. We have been determined to be rotable parts
Washington, DC 20590. will also post a report summarizing each that are capable of being installed on all
• Hand Delivery: Deliver to Mail substantive verbal contact we receive Model 747–8 and 747–8F series
address above between 9 a.m. and 5 about this proposed AD. airplanes. Therefore, the applicability of
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Document Created: 2018-11-06 10:34:44
Document Modified: 2018-11-06 10:34:44
| 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 September 17, 2018. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223. | |
| FR Citation | 83 FR 38091 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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