83 FR 48920 - Airworthiness Directives; Airbus SAS Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 189 (September 28, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 189 (September 28, 2018)
| Page Range | 48920-48924 | |
| FR Document | 2018-20951 |
[Federal Register Volume 83, Number 189 (Friday, September 28, 2018)] [Rules and Regulations] [Pages 48920-48924] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-20951] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD; Amendment 39-19436; AD 2018-20-02] RIN 2120-AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 98-18-24, which applied to certain Airbus SAS Model A320 series airplanes. AD 98- 18-24 required repetitive inspections to detect cracking in the inner flange of a certain door frame, and corrective actions, if necessary. AD 98-18-24 also provided an optional terminating action for the repetitive inspections. This AD continues to require the repetitive inspections of the inner flange of a certain door frame, with reduced repetitive inspection intervals, and corrective action if necessary. This AD was prompted by a report of cracks on the inner flange of a certain door frame, and by the results of a full scale fatigue test that indicated the intervals for the repetitive inspections required by AD 98-18-24 must be reduced. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 2, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 2, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; 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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0455. 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-2018- 0455; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647- 5527) is U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 98-18-24, Amendment 39-10740 (63 FR 49272, September 15, 1998) (``AD 98-18-24''). AD 98-18-24 applied to certain Airbus SAS Model A320 series airplanes. The NPRM published in the Federal Register on May 30, 2018 (83 FR 24690). The NPRM was prompted by a report of cracks on the inner flange of door frame 66 at stringer positions 18 and 20, and by the results of a full scale fatigue test that indicated the intervals for the repetitive inspections required by AD 98-18-24 must be reduced. The NPRM [[Page 48921]] proposed to continue to require the repetitive inspections of the inner flange of a certain door frame, with reduced repetitive inspection intervals, and corrective actions if necessary. We are issuing this AD to address fatigue cracking in the inner flange of door frame 66, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0128, dated July 24, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus SAS Model A320-211 and A320-231 airplanes. The MCAI states: During fatigue test on simulated flights, cracks developed on the inner flange of door frame 66 at stringer 18 and 20 positions. These cracks were located in the gusset plate attachment holes and were hidden by the plates. This condition, if not detected and corrected, could affect the structural integrity of the fuselage. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320-53-1071, later revised, to provide instructions to inspect and repair the gusset plate attachment holes at frame 66, at stringers 18, 20 and 22 both left hand (LH) and right hand (RH) side of the fuselage (hereafter collectively referred to as ``the attachment holes'' in this [EASA] AD), and [Airbus] SB A320-53-1072, providing instructions for reworking of the attachment holes. Consequently, DGAC France issued [French] AD 1996-234-087, later revised [which corresponds to FAA AD 98-18-24], requiring repetitive inspections and, depending on findings, repair of the attachment holes, and including reference to a reworking procedure, which constitutes optional terminating action for the repetitive inspections of the attachment holes. Since that [French] AD was issued, based on results from a full scale fatigue test, it was determined that the inspection intervals must be reduced. Airbus issued SB A320-53-1071 Revision 03, modifying the inspection threshold and intervals, and not changing the inspection instructions. For the reason described above, this [EASA] AD retains the requirement of DGAC France AD 1996-234-087 R1, which is superseded, and requires reduction of the repetitive inspection interval. 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- 0455. Comments We gave the public the opportunity to participate in developing this final rule. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017. This service information describes procedures for detailed inspections of the gusset plate attachment holes at door frame 66 for cracking and corrective action. Airbus also issued Service Bulletin A320-53-1072, Revision 02, dated May 5, 2016. This service information describes procedures for modification of the gusset frame attachment at door frame 66. 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. Costs of Compliance We estimate that this AD affects 3 airplanes of U.S. registry. The actions required by AD 98-18-24, and retained in this AD, take about 8 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 98-18-24 is $680 per product. We estimate that it would take about 19 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $4,845, or $1,615 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. In addition, we estimate that the optional terminating action would take about 20 work-hours per product, at an average labor rate of $85 per work-hour. Required parts costs would be about $60. Based on these figures, the estimated cost of the optional terminating action would be $1,760 per product. We also estimate that it would take about 1 work-hour per product to comply with the proposed reporting requirement in this AD. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of reporting the inspection results on U.S. operators to be $255, or $85 per product. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. 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 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 [[Page 48922]] delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 98-18-24, Amendment 39-10740 (63 FR 49272, September 15, 1998), and adding the following new AD: 2018-20-02 Airbus SAS: Amendment 39-19436; Docket No. FAA-2018-0455; Product Identifier 2017-NM-121-AD. (a) Effective Date This AD is effective November 2, 2018. (b) Affected ADs This AD replaces AD 98-18-24, Amendment 39-10740 (63 FR 49272, September 15, 1998) (``AD 98-18-24''). (c) Applicability This AD applies to Airbus SAS Model A320-211 and Model A320-231 airplanes, certificated in any category, serial numbers 0029, 0045, 0046, 0049 through 0057 inclusive, 0059, 0064, and 0065. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of cracks on the inner flange of door frame 66 at stringer positions 18 and 20, and by the results of a full scale fatigue test that indicated the intervals for the repetitive inspections required by AD 98-18-24 must be reduced. We are issuing this AD to address fatigue cracking in the inner flange of door frame 66, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Eddy Current Inspection, With No Changes This paragraph restates the requirements of paragraph (a) of AD 98-18-24, with no changes. For Model A320 series airplanes on which Airbus Modification 21778 (reference Airbus Service Bulletin A320- 53-1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996) has not been accomplished: Prior to the accumulation of 20,000 total flight cycles, or within 1 year after October 20, 1998 (the effective date of AD 98-18-24), whichever occurs later: Perform a rotating probe eddy current inspection to detect cracking around the edges of the gusset plate attachment holes of the inner flange of door frame 66, left and right, at stringer positions P18, P20, and P22, in accordance with Airbus Service Bulletin A320-53-1071, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996. If any crack is detected, prior to further flight, repair in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA. Repeat the inspection thereafter at intervals not to exceed 20,000 flight cycles. (h) Retained Optional Terminating Action, With No Changes This paragraph restates the optional terminating action of paragraph (b) of AD 98-18-24, with no changes. Modification of the gusset plate attachment holes of the inner flange of door frame 66, left and right (Airbus Modification 21778), in accordance with Airbus Service Bulletin A320-53-1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996, constitutes terminating action for the repetitive inspection requirements of paragraph (g) of this AD. (i) New Requirement of This AD: Repetitive Inspections At the applicable compliance time specified in figure 1 to paragraph (i) of this AD, do a rotating probe eddy current inspection to detect cracking around the edges of the gusset plate attachment holes of the inner flange of door frame 66, left and right, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017. Repeat the inspection thereafter at intervals not to exceed 10,900 flight cycles. [[Page 48923]] [GRAPHIC] [TIFF OMITTED] TR28SE18.001 (j) Corrective Actions (1) If, during any inspection required by paragraph (i) of this AD, any crack is found on a gusset plate attachment hole: Before further flight, repair the affected attachment hole, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017, except as required by paragraph (n) of this AD. (2) If, during any inspection required by paragraph (i) of this AD, any crack is found on any other hole of the gusset plate: Before further flight, contact the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); for approved repair instructions and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature. (k) Terminating Action for This AD (1) Repair of a gusset plate attachment hole area as required by paragraph (j)(1) of this AD terminates the repetitive inspections required by paragraph (i) of this AD for that attachment hole area on that airplane only. (2) Repair of any other hole of the gusset plate, as required by paragraph (j)(2) of this AD, does not terminate the repetitive inspections required by paragraph (i) of this AD for that airplane, unless specified otherwise in the repair instructions provided by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA. (3) Accomplishing the initial inspection required by paragraph (i) of this AD terminates the inspections required by paragraph (g) of this AD. (l) Optional Modification Modification of the gusset plate attachment holes of the inner flange of door frame 66, left and right, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1072, Revision 02, dated May 5, 2016, terminates the repetitive inspections required by paragraph (i) of this AD for that airplane. (m) Reporting Report the results of the inspection required by paragraph (i) of this AD that are done on or after the effective date of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), or submit the results to Airbus in accordance with the instructions of Airbus Service Bulletin A320-53- 1071, Revision 03, dated July 20, 2017. Submit the report within 30 days after accomplishing the inspection required by paragraph (i) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. If operators have reported findings as part of obtaining any corrective actions approved by the EASA DOA, operators are not required to report those findings as specified in this paragraph. (n) Service Information Exception Where Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 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 (q)(2) of this AD. (o) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53- 1071, Revision 01, dated July 4, 2002; or Airbus Service Bulletin A320-53-1071, Revision 02, dated May 5, 2016. (2) This paragraph provides credit for actions identified in paragraph (l) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53- 1072, dated November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996; or Airbus Service Bulletin A320-53-1072, Revision 01, dated July 4, 2002. (p) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to [[Page 48924]] respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (q) Other FAA AD Provisions (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 (r)(2) of this AD. Information may be emailed to: [email protected]. (i) 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. (ii) AMOCs approved previously for AD 98-18-24 are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (n) 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. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0128, dated July 24, 2017, 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-2018-0455. (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) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (s)(3) and (s)(4) of this AD. (s) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320-53-1071, Revision 03, dated July 20, 2017. (ii) Airbus Service Bulletin A320-53-1072, Revision 02, dated May 5, 2016. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; internet http://www.airbus.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Des Moines, Washington, on September 13, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-20951 Filed 9-27-18; 8:45 am] BILLING CODE 4910-13-P
![48920 Federal Register / Vol. 83, No. 189 / Friday, September 28, 2018 / Rules and Regulations
(e) Unsafe Condition Corporation, Technical Publications Dept., DATES: This AD is effective November 2,
This AD was prompted by the potential for P.O. Box 2206, Savannah, GA 31402–2206; 2018.
an un-annunciated failure of the bi- telephone: 800–810–4853; fax: 912–965– The Director of the Federal Register
directional data bus that sends critical signals 3520; email: pubs@gulfstream.com; internet: approved the incorporation by reference
from the flight control computer to the flight http://www.gulfstream.com/product-support/
technical-publications.
of certain publications listed in this AD
controls. This unsafe condition, if not as of November 2, 2018.
addressed, could result in the flight control (4) You may view this service information
at the FAA, Policy and Innovation Division, ADDRESSES: For service information
computer’s inability to identify when a
problematic flight control surface needs to be 901 Locust, Kansas City, Missouri 64106. For identified in this final rule, contact
damped, which could result in loss of control information on the availability of this Airbus SAS, Airworthiness Office—
of the airplane. material at the FAA, call (816) 329–4148. EIAS, Rond-Point Emile Dewoitine No:
(5) You may view this service information 2, 31700 Blagnac Cedex, France;
(f) Compliance that is incorporated by reference at the
telephone +33 5 61 93 36 96; fax +33 5
Comply with this AD within the National Archives and Records
Administration (NARA). For information on 61 93 44 51; email account.airworth-
compliance times specified, unless already
the availability of this material at NARA, call eas@airbus.com; internet http://
done.
202–741–6030, or go to: http:// www.airbus.com. You may view this
(g) Airplane Flight Manual Revisions www.archives.gov/federal-register/cfr/ibr- referenced service information at the
Within 30 days after October 15, 2018 (the locations.html. FAA, Transport Standards Branch, 2200
effective date of this AD), revise the Normal Issued in Kansas City, Missouri, on South 216th St., Des Moines, WA. For
Procedures and Abnormal Procedures September 20, 2018. information on the availability of this
sections of the airplane flight manual by material at the FAA, call 206–231–3195.
adding the information in Gulfstream Melvin J. Johnson,
Aircraft Certification Service, Deputy It is also available on the internet at
Aerospace G650 Airplane Flight Manual
Director, Policy and Innovation Division, http://www.regulations.gov by searching
Supplement No. G650–2018–01, dated
August 14, 2018; or Gulfstream Aerospace AIR–601. for and locating Docket No. FAA–2018–
G650ER Airplane Flight Manual Supplement [FR Doc. 2018–21103 Filed 9–27–18; 8:45 am] 0455.
No. G650ER–2018–01, dated August 14, BILLING CODE 4910–13–P Examining the AD Docket
2018; as applicable to the model
configuration of your airplane. You may examine the AD docket on
DEPARTMENT OF TRANSPORTATION the internet at http://
(h) Alternative Methods of Compliance
(AMOCs)
www.regulations.gov by searching for
Federal Aviation Administration and locating Docket No. FAA–2018–
(1) The Manager, Atlanta ACO Branch, 0455; or in person at Docket Operations
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures 14 CFR Part 39 between 9 a.m. and 5 p.m., Monday
found in 14 CFR 39.19. In accordance with through Friday, except Federal holidays.
[Docket No. FAA–2018–0455; Product The AD docket contains this final rule,
14 CFR 39.19, send your request to your Identifier 2017–NM–121–AD; Amendment
principal inspector or local Flight Standards 39–19436; AD 2018–20–02]
the regulatory evaluation, any
District Office, as appropriate. If sending comments received, and other
information directly to the manager of the RIN 2120–AA64 information. The address for Docket
certification office, send it to the attention of Operations (phone: 800–647–5527) is
the person identified in paragraph (i) of this Airworthiness Directives; Airbus SAS U.S. Department of Transportation,
AD. Airplanes Docket Operations, M–30, West
(2) Before using any approved AMOC,
notify your appropriate principal inspector, AGENCY: Federal Aviation Building Ground Floor, Room W12–140,
or lacking a principal inspector, the manager Administration (FAA), Department of 1200 New Jersey Avenue SE,
of the local flight standards district office/ Transportation (DOT). Washington, DC 20590.
certificate holding district office. ACTION: Final rule. FOR FURTHER INFORMATION CONTACT:
(i) Related Information Sanjay Ralhan, Aerospace Engineer,
SUMMARY: We are superseding International Section, Transport
For more information about this AD,
contact Myles Jalalian, Aerospace Engineer,
Airworthiness Directive (AD) 98–18–24, Standards Branch, FAA; 2200 South
Systems and Equipment Section, AIR–7A3, which applied to certain Airbus SAS 216th St., Des Moines, WA 98198;
Atlanta ACO Branch, FAA, 1701 Columbia Model A320 series airplanes. AD 98– telephone and fax 206–231–3223.
Avenue, College Park, GA 30337; phone: 18–24 required repetitive inspections to SUPPLEMENTARY INFORMATION:
404–474–5572; fax: 404–474–5606; email: detect cracking in the inner flange of a
Myles.Jalalian@faa.gov. certain door frame, and corrective Discussion
(j) Material Incorporated by Reference actions, if necessary. AD 98–18–24 also We issued a notice of proposed
provided an optional terminating action rulemaking (NPRM) to amend 14 CFR
(1) The Director of the Federal Register
approved the incorporation by reference
for the repetitive inspections. This AD part 39 to supersede AD 98–18–24,
(IBR) of the service information listed in this continues to require the repetitive Amendment 39–10740 (63 FR 49272,
paragraph under 5 U.S.C. 552(a) and 1 CFR inspections of the inner flange of a September 15, 1998) (‘‘AD 98–18–24’’).
part 51. certain door frame, with reduced AD 98–18–24 applied to certain Airbus
(2) You must use this service information repetitive inspection intervals, and SAS Model A320 series airplanes. The
as applicable to do the actions required by corrective action if necessary. This AD NPRM published in the Federal
this AD, unless the AD specifies otherwise. was prompted by a report of cracks on Register on May 30, 2018 (83 FR 24690).
(i) Gulfstream Aerospace G650 Airplane the inner flange of a certain door frame, The NPRM was prompted by a report of
daltland on DSKBBV9HB2PROD with RULES
Flight Manual, Supplement No. G650–2018– and by the results of a full scale fatigue cracks on the inner flange of door frame
01, dated August 14, 2018.
(ii) Gulfstream Aerospace G650ER Airplane
test that indicated the intervals for the 66 at stringer positions 18 and 20, and
Flight Manual, Supplement No. G650ER– repetitive inspections required by AD by the results of a full scale fatigue test
2018–01, dated August 14, 2018. 98–18–24 must be reduced. We are that indicated the intervals for the
(3) For service information identified in issuing this AD to address the unsafe repetitive inspections required by AD
this AD, contact Gulfstream Aerospace condition on these products. 98–18–24 must be reduced. The NPRM
VerDate Sep<11>2014 17:35 Sep 27, 2018 Jkt 244001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\28SER1.SGM 28SER1](https://thefederalregister.org/doc/83_FR_49109/page/1.svg)
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proposed to continue to require the or on the determination of the cost to We also estimate that it would take
repetitive inspections of the inner flange the public. about 1 work-hour per product to
of a certain door frame, with reduced comply with the proposed reporting
Conclusion
repetitive inspection intervals, and requirement in this AD. The average
corrective actions if necessary. We are We reviewed the relevant data and labor rate is $85 per hour. Based on
issuing this AD to address fatigue determined that air safety and the these figures, we estimate the cost of
cracking in the inner flange of door public interest require adopting this reporting the inspection results on U.S.
frame 66, which could result in reduced final rule as proposed, except for minor operators to be $255, or $85 per product.
structural integrity of the airplane. editorial changes. We have determined
that these minor changes: Paperwork Reduction Act
The European Aviation Safety Agency
(EASA), which is the Technical Agent • Are consistent with the intent that A federal agency may not conduct or
for the Member States of the European was proposed in the NPRM for sponsor, and a person is not required to
Union, has issued EASA AD 2017–0128, addressing the unsafe condition; and respond to, nor shall a person be subject
dated July 24, 2017 (referred to after this • Do not add any additional burden to penalty for failure to comply with a
as the Mandatory Continuing upon the public than was already collection of information subject to the
Airworthiness Information, or ‘‘the proposed in the NPRM. requirements of the Paperwork
MCAI’’), to correct an unsafe condition Reduction Act unless that collection of
Related Service Information Under 1 information displays a current valid
for certain Airbus SAS Model A320–211 CFR Part 51
and A320–231 airplanes. The MCAI OMB control number. The control
states: Airbus has issued Service Bulletin number for the collection of information
A320–53–1071, Revision 03, dated July required by this AD is 2120–0056. The
During fatigue test on simulated flights, 20, 2017. This service information paperwork cost associated with this AD
cracks developed on the inner flange of door
frame 66 at stringer 18 and 20 positions. describes procedures for detailed has been detailed in the Costs of
These cracks were located in the gusset plate inspections of the gusset plate Compliance section of this document
attachment holes and were hidden by the attachment holes at door frame 66 for and includes time for reviewing
plates. cracking and corrective action. instructions, as well as completing and
This condition, if not detected and Airbus also issued Service Bulletin reviewing the collection of information.
corrected, could affect the structural integrity A320–53–1072, Revision 02, dated May Therefore, all reporting associated with
of the fuselage. 5, 2016. This service information this AD is mandatory. Comments
To address this potential unsafe condition, describes procedures for modification of concerning the accuracy of this burden
Airbus issued Service Bulletin (SB) A320– the gusset frame attachment at door and suggestions for reducing the burden
53–1071, later revised, to provide
instructions to inspect and repair the gusset
frame 66. should be directed to the FAA at 800
plate attachment holes at frame 66, at This service information is reasonably Independence Ave. SW, Washington,
stringers 18, 20 and 22 both left hand (LH) available because the interested parties DC 20591, ATTN: Information
and right hand (RH) side of the fuselage have access to it through their normal Collection Clearance Officer, AES–200.
(hereafter collectively referred to as ‘‘the course of business or by the means
Authority for This Rulemaking
attachment holes’’ in this [EASA] AD), and identified in the ADDRESSES section.
[Airbus] SB A320–53–1072, providing Title 49 of the United States Code
instructions for reworking of the attachment Costs of Compliance specifies the FAA’s authority to issue
holes. We estimate that this AD affects 3 rules on aviation safety. Subtitle I,
Consequently, DGAC France issued airplanes of U.S. registry. section 106, describes the authority of
[French] AD 1996–234–087, later revised The actions required by AD 98–18–24, the FAA Administrator. Subtitle VII:
[which corresponds to FAA AD 98–18–24],
requiring repetitive inspections and,
and retained in this AD, take about 8 Aviation Programs, describes in more
depending on findings, repair of the work-hours per product, at an average detail the scope of the Agency’s
attachment holes, and including reference to labor rate of $85 per work-hour. Based authority.
a reworking procedure, which constitutes on these figures, the estimated cost of We are issuing this rulemaking under
optional terminating action for the repetitive the actions that are required by AD 98– the authority described in Subtitle VII,
inspections of the attachment holes. 18–24 is $680 per product. Part A, Subpart III, Section 44701:
Since that [French] AD was issued, based We estimate that it would take about ‘‘General requirements.’’ Under that
on results from a full scale fatigue test, it was 19 work-hours per product to comply section, Congress charges the FAA with
determined that the inspection intervals must with the basic requirements of this AD. promoting safe flight of civil aircraft in
be reduced. Airbus issued SB A320–53–1071
The average labor rate is $85 per work- air commerce by prescribing regulations
Revision 03, modifying the inspection
threshold and intervals, and not changing the hour. Based on these figures, we for practices, methods, and procedures
inspection instructions. estimate the cost of this AD on U.S. the Administrator finds necessary for
For the reason described above, this operators to be $4,845, or $1,615 per safety in air commerce. This regulation
[EASA] AD retains the requirement of DGAC product. is within the scope of that authority
France AD 1996–234–087 R1, which is We have received no definitive data because it addresses an unsafe condition
superseded, and requires reduction of the that would enable us to provide cost that is likely to exist or develop on
repetitive inspection interval. estimates for the on-condition actions products identified in this rulemaking
You may examine the MCAI in the specified in this AD. action.
AD docket on the internet at http:// In addition, we estimate that the This AD is issued in accordance with
www.regulations.gov by searching for optional terminating action would take authority delegated by the Executive
about 20 work-hours per product, at an Director, Aircraft Certification Service,
daltland on DSKBBV9HB2PROD with RULES
and locating Docket No. FAA–2018–
0455. average labor rate of $85 per work-hour. as authorized by FAA Order 8000.51C.
Required parts costs would be about In accordance with that order, issuance
Comments $60. Based on these figures, the of ADs is normally a function of the
We gave the public the opportunity to estimated cost of the optional Compliance and Airworthiness
participate in developing this final rule. terminating action would be $1,760 per Division, but during this transition
We received no comments on the NPRM product. period, the Executive Director has
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![48922 Federal Register / Vol. 83, No. 189 / Friday, September 28, 2018 / Rules and Regulations
delegated the authority to issue ADs § 39.13 [Amended] Airbus Service Bulletin A320–53–1072,
applicable to transport category ■ 2. The FAA amends § 39.13 by dated November 7, 1995, as revised by
airplanes and associated appliances to Change Notice 0A, dated July 5, 1996) has
removing Airworthiness Directive (AD)
the Director of the System Oversight not been accomplished: Prior to the
98–18–24, Amendment 39–10740 (63 accumulation of 20,000 total flight cycles, or
Division. FR 49272, September 15, 1998), and within 1 year after October 20, 1998 (the
Regulatory Findings adding the following new AD: effective date of AD 98–18–24), whichever
We determined that this AD will not 2018–20–02 Airbus SAS: Amendment 39– occurs later: Perform a rotating probe eddy
19436; Docket No. FAA–2018–0455; current inspection to detect cracking around
have federalism implications under Product Identifier 2017–NM–121–AD. the edges of the gusset plate attachment holes
Executive Order 13132. This AD will of the inner flange of door frame 66, left and
not have a substantial direct effect on (a) Effective Date
right, at stringer positions P18, P20, and P22,
the States, on the relationship between This AD is effective November 2, 2018. in accordance with Airbus Service Bulletin
the national government and the States, (b) Affected ADs A320–53–1071, dated November 7, 1995, as
or on the distribution of power and revised by Change Notice 0A, dated July 5,
responsibilities among the various This AD replaces AD 98–18–24,
1996. If any crack is detected, prior to further
Amendment 39–10740 (63 FR 49272,
levels of government. September 15, 1998) (‘‘AD 98–18–24’’). flight, repair in accordance with a method
For the reasons discussed above, I approved by the Manager, International
certify that this AD: (c) Applicability Section, Transport Standards Branch, FAA.
1. Is not a ‘‘significant regulatory This AD applies to Airbus SAS Model Repeat the inspection thereafter at intervals
action’’ under Executive Order 12866; A320–211 and Model A320–231 airplanes, not to exceed 20,000 flight cycles.
2. Is not a ‘‘significant rule’’ under the certificated in any category, serial numbers (h) Retained Optional Terminating Action,
DOT Regulatory Policies and Procedures 0029, 0045, 0046, 0049 through 0057
With No Changes
(44 FR 11034, February 26, 1979); inclusive, 0059, 0064, and 0065.
This paragraph restates the optional
3. Will not affect intrastate aviation in (d) Subject terminating action of paragraph (b) of AD 98–
Alaska; and Air Transport Association (ATA) of 18–24, with no changes. Modification of the
4. Will not have a significant America Code 53, Fuselage. gusset plate attachment holes of the inner
economic impact, positive or negative, flange of door frame 66, left and right (Airbus
on a substantial number of small entities (e) Reason
Modification 21778), in accordance with
under the criteria of the Regulatory This AD was prompted by a report of Airbus Service Bulletin A320–53–1072,
Flexibility Act. cracks on the inner flange of door frame 66 dated November 7, 1995, as revised by
at stringer positions 18 and 20, and by the Change Notice 0A, dated July 5, 1996,
List of Subjects in 14 CFR Part 39 results of a full scale fatigue test that constitutes terminating action for the
indicated the intervals for the repetitive
Air transportation, Aircraft, Aviation repetitive inspection requirements of
inspections required by AD 98–18–24 must
safety, Incorporation by reference, paragraph (g) of this AD.
be reduced. We are issuing this AD to
Safety. address fatigue cracking in the inner flange (i) New Requirement of This AD: Repetitive
Adoption of the Amendment of door frame 66, which could result in Inspections
reduced structural integrity of the airplane. At the applicable compliance time
Accordingly, under the authority
(f) Compliance specified in figure 1 to paragraph (i) of this
delegated to me by the Administrator,
Comply with this AD within the AD, do a rotating probe eddy current
the FAA amends 14 CFR part 39 as inspection to detect cracking around the
follows: compliance times specified, unless already
done. edges of the gusset plate attachment holes of
the inner flange of door frame 66, left and
PART 39—AIRWORTHINESS (g) Retained Eddy Current Inspection, With right, in accordance with the
DIRECTIVES No Changes Accomplishment Instructions of Airbus
This paragraph restates the requirements of Service Bulletin A320–53–1071, Revision 03,
■ 1. The authority citation for part 39 dated July 20, 2017. Repeat the inspection
paragraph (a) of AD 98–18–24, with no
continues to read as follows: changes. For Model A320 series airplanes on thereafter at intervals not to exceed 10,900
Authority: 49 U.S.C. 106(g), 40113, 44701. which Airbus Modification 21778 (reference flight cycles.
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![48924 Federal Register / Vol. 83, No. 189 / Friday, September 28, 2018 / Rules and Regulations
respond to, nor shall a person be subject to information. This MCAI may be found in the ACTION: Final rule.
a penalty for failure to comply with a AD docket on the internet at http://
collection of information subject to the www.regulations.gov by searching for and SUMMARY: We are adopting a new
requirements of the Paperwork Reduction locating Docket No. FAA–2018–0455. airworthiness directive (AD) for all
Act unless that collection of information (2) For more information about this AD, Dassault Aviation Model FALCON 2000
displays a current valid OMB Control contact Sanjay Ralhan, Aerospace Engineer, airplanes. This AD was prompted by a
Number. The OMB Control Number for this International Section, Transport Standards
determination that new or more
information collection is 2120–0056. Public Branch, FAA; 2200 South 216th St., Des
reporting for this collection of information is Moines, WA 98198; telephone and fax 206– restrictive airworthiness limitations are
estimated to be approximately 1 hour per 231–3223. necessary. This AD requires revising the
response, including the time for reviewing (3) Service information identified in this maintenance or inspection program, as
instructions, completing and reviewing the AD that is not incorporated by reference is applicable, to incorporate new
collection of information. All responses to available at the addresses specified in maintenance requirements and
this collection of information are mandatory. paragraphs (s)(3) and (s)(4) of this AD. airworthiness limitations. We are
Comments concerning the accuracy of this issuing this AD to address the unsafe
(s) Material Incorporated by Reference
burden and suggestions for reducing the condition on these products.
burden should be directed to the FAA at: 800 (1) The Director of the Federal Register
Independence Ave. SW, Washington, DC approved the incorporation by reference DATES: This AD is effective November 2,
20591, Attn: Information Collection (IBR) of the service information listed in this 2018.
Clearance Officer, AES–200. paragraph under 5 U.S.C. 552(a) and 1 CFR The Director of the Federal Register
part 51. approved the incorporation by reference
(q) Other FAA AD Provisions (2) You must use this service information of a certain publication listed in this AD
(1) Alternative Methods of Compliance as applicable to do the actions required by as of November 2, 2018.
(AMOCs): The Manager, International this AD, unless this AD specifies otherwise.
Section, Transport Standards Branch, FAA, (i) Airbus Service Bulletin A320–53–1071, ADDRESSES: For service information
has the authority to approve AMOCs for this Revision 03, dated July 20, 2017. identified in this final rule, contact
AD, if requested using the procedures found (ii) Airbus Service Bulletin A320–53–1072, Dassault Falcon Jet Corporation,
in 14 CFR 39.19. In accordance with 14 CFR Revision 02, dated May 5, 2016. Teterboro Airport, P.O. Box 2000, South
39.19, send your request to your principal (3) For service information identified in Hackensack, NJ 07606; telephone 201–
inspector or local Flight Standards District this AD, contact Airbus SAS, Airworthiness 440–6700; internet http://
Office, as appropriate. If sending information Office—EIAS, Rond-Point Emile Dewoitine www.dassaultfalcon.com. You may
directly to the International Section, send it No: 2, 31700 Blagnac Cedex, France; view this service information at the
to the attention of the person identified in telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
FAA, Transport Standards Branch, 2200
paragraph (r)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOC- airbus.com; internet http://www.airbus.com. South 216th St., Des Moines, WA. For
REQUESTS@faa.gov. (4) You may view this service information information on the availability of this
(i) Before using any approved AMOC, at the FAA, Transport Standards Branch, material at the FAA, call 206–231–3195.
notify your appropriate principal inspector, 2200 South 216th St., Des Moines, WA. For It is also available on the internet at
or lacking a principal inspector, the manager information on the availability of this http://www.regulations.gov by searching
of the local flight standards district office/ material at the FAA, call 206–231–3195. for and locating Docket No. FAA–2018–
certificate holding district office. (5) You may view this service information 0306.
(ii) AMOCs approved previously for AD that is incorporated by reference at the
98–18–24 are approved as AMOCs for the National Archives and Records Examining the AD Docket
corresponding provisions of this AD. Administration (NARA). For information on
the availability of this material at NARA, call
You may examine the AD docket on
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement 202–741–6030, or go to: http:// the internet at http://
in this AD to obtain corrective actions from www.archives.gov/federal-register/cfr/ibr- www.regulations.gov by searching for
a manufacturer, the action must be locations.html. and locating Docket No. FAA–2018–
accomplished using a method approved by Issued in Des Moines, Washington, on
0306; or in person at Docket Operations
the Manager, International Section, Transport September 13, 2018. between 9 a.m. and 5 p.m., Monday
Standards Branch, FAA; or the EASA; or through Friday, except Federal holidays.
Airbus SAS’s EASA DOA. If approved by the Michael Kaszycki,
The AD docket contains this final rule,
DOA, the approval must include the DOA- Acting Director, System Oversight Division,
Aircraft Certification Service.
the regulatory evaluation, any
authorized signature.
comments received, and other
(3) Required for Compliance (RC): Except [FR Doc. 2018–20951 Filed 9–27–18; 8:45 am]
as required by paragraph (n) of this AD: If information. The address for Docket
BILLING CODE 4910–13–P
any service information contains procedures Operations (phone: 800–647–5527) is
or tests that are identified as RC, those U.S. Department of Transportation,
procedures and tests must be done to comply Docket Operations, M–30, West
DEPARTMENT OF TRANSPORTATION
with this AD; any procedures or tests that are Building Ground Floor, Room W12–140,
not identified as RC are recommended. Those Federal Aviation Administration 1200 New Jersey Avenue SE,
procedures and tests that are not identified Washington, DC 20590.
as RC may be deviated from using accepted
14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: Tom
methods in accordance with the operator’s
maintenance or inspection program without Rodriguez, Aerospace Engineer,
[Docket No. FAA–2018–0306; Product
obtaining approval of an AMOC, provided Identifier 2018–NM–039–AD; Amendment
International Section, Transport
the procedures and tests identified as RC can 39–19426; AD 2018–19–25] Standards Branch, FAA, 2200 South
be done and the airplane can be put back in 216th St., Des Moines, WA 98198;
an airworthy condition. Any substitutions or RIN 2120–AA64 telephone and fax 206–231–3226.
daltland on DSKBBV9HB2PROD with RULES
changes to procedures or tests identified as
Airworthiness Directives; Dassault SUPPLEMENTARY INFORMATION:
RC require approval of an AMOC.
Aviation Airplanes Discussion
(r) Related Information
(1) Refer to Mandatory Continuing AGENCY: Federal Aviation We issued a notice of proposed
Airworthiness Information (MCAI) EASA AD Administration (FAA), Department of rulemaking (NPRM) to amend 14 CFR
2017–0128, dated July 24, 2017, for related Transportation (DOT). part 39 by adding an AD that would
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Document Created: 2018-09-28 01:22:55
Document Modified: 2018-09-28 01:22:55
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 2, 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 48920 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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