83 FR 39377 - Airworthiness Directives; Airbus SAS Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 154 (August 9, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 154 (August 9, 2018)
| Page Range | 39377-39380 | |
| FR Document | 2018-16733 |
[Federal Register Volume 83, Number 154 (Thursday, August 9, 2018)] [Proposed Rules] [Pages 39377-39380] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-16733] [[Page 39377]] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0705; Product Identifier 2018-NM-077-AD] RIN 2120-AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This proposed AD was prompted by a report that during removal of left-hand (LH) gear rib 5, four failed fasteners were discovered. This proposed AD would require a one-time ultrasonic inspection of the LH and right-hand (RH) wing rib 5-to-rear spar attachments for cracked or failed fasteners, and if necessary, a detailed inspection of the gear rib 5 and spar web for cracks and damage, a rotating probe test of the gear rib and spar web bolt holes for cracks and damage, reaming the gear rib and the spar web bolt holes, and replacement of cracked or failed fasteners. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 24, 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 SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: [email protected]; 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. 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- 0705; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 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; phone 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-2018-0705; Product Identifier 2018-NM-077-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018-0102, dated April 27, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus SAS Model A321-111, - 112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states: During removal of the left hand (LH) rib 5, two of the fasteners (bolts) attaching the rib to the wing inner rear spar were found to have failed and two more failed during their removal. Two of the bolts were found separated from the bolt shanks when the overcoat sealant was being removed, and the other two bolt heads broke away during removal. This condition, if not detected and corrected, could reduce the structural integrity of the wing. To address this possible unsafe condition, Airbus issued [Service Bulletin] SB A320-57-1167 to provide inspection instructions. After that SB was issued, a potential manufacturing issue was identified on early production A321 [airplanes] concerning reports of fasteners ``jamming'' during installation on spar assemblies. A process change was introduced in production line, and SB A320-57-1167 was revised, changing the affected population to include all A321 aeroplanes delivered before the introduction of that process change. For the reasons described above, this [EASA] AD requires a one- time special detailed [ultrasonic] inspection (SDI) of the wing rib 5-to-rear spar attachments, both LH and right hand (RH) wings, [and if necessary, a detailed inspection of the gear rib 5 and spar web for cracks and damage (cracks along the length of the bolt or broken bolt), a rotating probe test of the gear rib and spar web bolt holes for cracks and damage (cracks in the bolt holes), reaming the gear rib and the spar web bolt holes] and, depending on findings, accomplishment of a repair [replacement of cracked or failed (broken) fasteners (bolts)]. This [EASA] AD also requires the reporting of findings. 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- 0705. Related Service Information Under 1 CFR Part 51 Airbus SAS has issued Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. This service information describes procedures for a one-time special detailed (ultrasonic) inspection of the LH and RH wing rib 5-to-rear spar attachments for cracked or failed (broken) fasteners (bolts), and if necessary, a detailed inspection of the gear- rib-5 and spar web for cracks and damage (cracks along the length of the bolt or broken bolt), a rotating probe test of the gear rib and spar web bolt holes for cracks and damage (cracks in the bolt holes), reaming the gear rib and the spar web bolt holes, and replacement of the cracked or damaged (broken) fasteners (bolts). 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 This product has been approved by the aviation authority of another country, and is approved for operation [[Page 39378]] 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 the relevant information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. Proposed Requirements of This NPRM This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the MCAI or Service Information.'' This proposed AD also would require sending the inspection results to Airbus SAS. Differences Between This Proposed AD and the MCAI or Service Information The MCAI specifies credit for actions accomplished in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320- 57-1167, dated August 10, 2011. The MCAI also discusses a potential manufacturing issue that was identified on early production Model A321 airplanes concerning reports of fasteners ``jamming'' during installation on spar assemblies. The corrective action specified in Airbus Service Bulletin A320-57-1167, dated August 10, 2011, includes the same process that produced ``jamming'' previously. Therefore, this proposed AD does not include credit for actions accomplished using the Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, dated August 10, 2011. Explanation of Change to Applicability We have revised the applicability of this AD to identify model designations as published in the most recent type certificate data sheet for the affected model. Costs of Compliance We estimate that this proposed AD affects 29 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- 16 work-hours x $85 per hour = $1,360........................ $0 $1,360 $39,440 ---------------------------------------------------------------------------------------------------------------- We estimate that it would take about 1 work-hour per product to comply with the proposed reporting requirement in this proposed 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 $2,465, or $85 per product. We estimate the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. We have no way of determining the number of aircraft that might need these on-condition actions: Estimated Costs of On-Condition Actions ------------------------------------------------------------------------ Cost per Labor cost Parts cost product ------------------------------------------------------------------------ 20 work-hours x $85 per hour = $1,700. $0 $1,700 ------------------------------------------------------------------------ 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 NPRM is 2120- 0056. The paperwork cost associated with this NPRM 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 NPRM 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 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; [[Page 39379]] 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Airbus SAS: Docket No. FAA-2018-0705; Product Identifier 2018-NM- 077-AD. (a) Comments Due Date We must receive comments by September 24, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category, as identified in Airbus Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report that during removal of left- hand (LH) gear rib 5, four failed fasteners (bolts attaching the gear rib to the wing inner rear spar) were discovered. We are issuing this AD to detect and correct cracked or failed (broken) fasteners (bolts) of the rib 5-to-rear spar attachment, which could lead to reduced structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of the Rib 5-to-Rear Spar Attachment Fasteners (Bolts) Within 30 months after the effective date of this AD, do a special detailed (ultrasonic) inspection of the LH and right-hand (RH) wing rib 5-to-rear spar attachment fasteners (bolts) for cracked or failed (broken) fasteners (bolts), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. (h) Replacement of Cracked or Failed Fasteners (Bolts) If any cracked or failed (broken) fastener (bolt) is found during any inspection required by paragraph (g) of this AD, before further flight, do the actions specified in paragraph (h)(1), (h)(2), (h)(3) and (h)(4) of this AD, as applicable. (1) Do a detailed inspection of the gear rib 5 and spar web for cracks and damage (cracks along the length of the bolt or broken bolt), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. If any crack or damage is found during any inspection required by this paragraph, before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA); and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA-authorized signature. (2) If no cracks or damage are found during any inspection required by paragraph (h)(1) of this AD: Do a rotating probe test of the gear rib and spar web bolt holes for cracks and damage (cracks in the bolt holes), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. If any crack or damage is found during any inspection required by this paragraph, before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA; and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA authorized signature. (3) If no cracks or damage are found during any inspection required by paragraph (h)(2) of this AD: Ream the gear rib and the spar web bolt holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. If an oversize larger than 0.794 millimeter (0.0313 inch) is required, before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA; and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA authorized signature. (4) Replace any cracked or failed fasteners (bolts) in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. (i) Reporting Within 90 days after the special detailed inspection required by paragraph (g) of this AD, or within 30 days after the effective date of this AD, whichever occurs later, report the inspection results (both positive and negative) to Airbus SAS in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018. 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. (j) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to 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. (k) 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 (l)(2) of this AD. Information may be emailed to: [email protected]. 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 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 (i) of this AD: If any service information contains procedures or [[Page 39380]] 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018-0102, dated April 27, 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-2018-0705. (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; phone and fax: 206-231-3223. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: [email protected]; 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 27, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-16733 Filed 8-8-18; 8:45 am] BILLING CODE 4910-13-P
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DEPARTMENT OF TRANSPORTATION FAA, Transport Standards Branch, 2200 separated from the bolt shanks when the
South 216th St., Des Moines, WA. For overcoat sealant was being removed, and the
Federal Aviation Administration information on the availability of this other two bolt heads broke away during
material at the FAA, call 206–231–3195. removal.
This condition, if not detected and
14 CFR Part 39 corrected, could reduce the structural
Examining the AD Docket
[Docket No. FAA–2018–0705; Product integrity of the wing.
You may examine the AD docket on To address this possible unsafe condition,
Identifier 2018–NM–077–AD]
the internet at http:// Airbus issued [Service Bulletin] SB A320–
RIN 2120–AA64 www.regulations.gov by searching for 57–1167 to provide inspection instructions.
and locating Docket No. FAA–2018– After that SB was issued, a potential
Airworthiness Directives; Airbus SAS 0705; or in person at Docket Operations manufacturing issue was identified on early
Airplanes between 9 a.m. and 5 p.m., Monday production A321 [airplanes] concerning
through Friday, except Federal holidays. reports of fasteners ‘‘jamming’’ during
AGENCY: Federal Aviation installation on spar assemblies. A process
Administration (FAA), DOT. The AD docket contains this NPRM, the
change was introduced in production line,
regulatory evaluation, any comments
ACTION: Notice of proposed rulemaking and SB A320–57–1167 was revised, changing
received, and other information. The the affected population to include all A321
(NPRM).
street address for Docket Operations aeroplanes delivered before the introduction
SUMMARY: We propose to adopt a new (phone: 800–647–5527) is in the of that process change.
airworthiness directive (AD) for certain ADDRESSES section. Comments will be For the reasons described above, this
Airbus SAS Model A321–111, –112, available in the AD docket shortly after [EASA] AD requires a one-time special
–131, –211, –212, –213, –231, and –232 receipt. detailed [ultrasonic] inspection (SDI) of the
airplanes. This proposed AD was FOR FURTHER INFORMATION CONTACT: wing rib 5-to-rear spar attachments, both LH
and right hand (RH) wings, [and if necessary,
prompted by a report that during Sanjay Ralhan, Aerospace Engineer,
a detailed inspection of the gear rib 5 and
removal of left-hand (LH) gear rib 5, four International Section, Transport spar web for cracks and damage (cracks along
failed fasteners were discovered. This Standards Branch, FAA, 2200 South the length of the bolt or broken bolt), a
proposed AD would require a one-time 216th St., Des Moines, WA 98198; rotating probe test of the gear rib and spar
ultrasonic inspection of the LH and phone and fax: 206–231–3223. web bolt holes for cracks and damage (cracks
right-hand (RH) wing rib 5-to-rear spar SUPPLEMENTARY INFORMATION: in the bolt holes), reaming the gear rib and
attachments for cracked or failed the spar web bolt holes] and, depending on
Comments Invited findings, accomplishment of a repair
fasteners, and if necessary, a detailed
inspection of the gear rib 5 and spar web We invite you to send any written [replacement of cracked or failed (broken)
relevant data, views, or arguments about fasteners (bolts)]. This [EASA] AD also
for cracks and damage, a rotating probe requires the reporting of findings.
test of the gear rib and spar web bolt this proposal. Send your comments to
holes for cracks and damage, reaming an address listed under the ADDRESSES You may examine the MCAI in the
the gear rib and the spar web bolt holes, section. Include ‘‘Docket No. FAA– AD docket on the internet at http://
and replacement of cracked or failed 2018–0705; Product Identifier 2018– www.regulations.gov by searching for
fasteners. We are proposing this AD to NM–077–AD’’ at the beginning of your and locating Docket No. FAA–2018–
address the unsafe condition on these comments. We specifically invite 0705.
products. comments on the overall regulatory, Related Service Information Under 1
economic, environmental, and energy CFR Part 51
DATES: We must receive comments on
aspects of this NPRM. We will consider
this proposed AD by September 24, Airbus SAS has issued Service
all comments received by the closing
2018. Bulletin A320–57–1167, Revision 01,
date and may amend this NPRM
ADDRESSES: You may send comments, because of those comments. dated January 16, 2018. This service
using the procedures found in 14 CFR We will post all comments we information describes procedures for a
11.43 and 11.45, by any of the following receive, without change, to http:// one-time special detailed (ultrasonic)
methods: www.regulations.gov, including any inspection of the LH and RH wing rib
• Federal eRulemaking Portal: Go to personal information you provide. We 5-to-rear spar attachments for cracked or
http://www.regulations.gov. Follow the will also post a report summarizing each failed (broken) fasteners (bolts), and if
instructions for submitting comments. substantive verbal contact we receive necessary, a detailed inspection of the
• Fax: 202–493–2251. about this NPRM. gear-rib-5 and spar web for cracks and
• Mail: U.S. Department of damage (cracks along the length of the
Transportation, Docket Operations, M– Discussion bolt or broken bolt), a rotating probe test
30, West Building Ground Floor, Room The European Aviation Safety Agency of the gear rib and spar web bolt holes
W12–140, 1200 New Jersey Avenue SE, (EASA), which is the Technical Agent for cracks and damage (cracks in the
Washington, DC 20590. for the Member States of the European bolt holes), reaming the gear rib and the
• Hand Delivery: Deliver to Mail Union, has issued EASA AD 2018–0102, spar web bolt holes, and replacement of
address above between 9 a.m. and 5 dated April 27, 2018 (referred to after the cracked or damaged (broken)
p.m., Monday through Friday, except this as the Mandatory Continuing fasteners (bolts). This service
Federal holidays. Airworthiness Information, or ‘‘the information is reasonably available
For service information identified in
sradovich on DSK3GMQ082PROD with PROPOSALS
MCAI’’), to correct an unsafe condition because the interested parties have
this NPRM, contact Airbus SAS, for certain Airbus SAS Model A321– access to it through their normal course
Airworthiness Office—EAL, Rond-Point 111, –112, –131, –211, –212, –213, –231, of business or by the means identified
Emile Dewoitine No: 2, 31700 Blagnac and –232 airplanes. The MCAI states: in the ADDRESSES section.
Cedex, France; phone: +33 5 61 93 36
During removal of the left hand (LH) rib 5, FAA’s Determination
96; fax: +33 5 61 93 45 80; email: two of the fasteners (bolts) attaching the rib
airworthiness.A330-A340@airbus.com; to the wing inner rear spar were found to This product has been approved by
internet: http://www.airbus.com. You have failed and two more failed during their the aviation authority of another
may view this service information at the removal. Two of the bolts were found country, and is approved for operation
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2. Is not a ‘‘significant rule’’ under the (g) Inspection of the Rib 5-to-Rear Spar Service Bulletin A320–57–1167, Revision 01,
DOT Regulatory Policies and Procedures Attachment Fasteners (Bolts) dated January 16, 2018.
(44 FR 11034, February 26, 1979); Within 30 months after the effective date (i) Reporting
of this AD, do a special detailed (ultrasonic)
3. Will not affect intrastate aviation in inspection of the LH and right-hand (RH)
Within 90 days after the special detailed
Alaska; and inspection required by paragraph (g) of this
wing rib 5-to-rear spar attachment fasteners
AD, or within 30 days after the effective date
4. Will not have a significant (bolts) for cracked or failed (broken) fasteners
of this AD, whichever occurs later, report the
economic impact, positive or negative, (bolts), in accordance with the
inspection results (both positive and
on a substantial number of small entities Accomplishment Instructions of Airbus negative) to Airbus SAS in accordance with
Service Bulletin A320–57–1167, Revision 01,
under the criteria of the Regulatory the Accomplishment Instructions of Airbus
dated January 16, 2018. Service Bulletin A320–57–1167, Revision 01,
Flexibility Act.
(h) Replacement of Cracked or Failed dated January 16, 2018. If operators have
List of Subjects in 14 CFR Part 39 Fasteners (Bolts) reported findings as part of obtaining any
corrective actions approved by the EASA
Air transportation, Aircraft, Aviation If any cracked or failed (broken) fastener
DOA, operators are not required to report
(bolt) is found during any inspection
safety, Incorporation by reference, those findings as specified in this paragraph.
required by paragraph (g) of this AD, before
Safety. further flight, do the actions specified in (j) Paperwork Reduction Act Burden
The Proposed Amendment paragraph (h)(1), (h)(2), (h)(3) and (h)(4) of Statement
this AD, as applicable. A federal agency may not conduct or
Accordingly, under the authority (1) Do a detailed inspection of the gear rib sponsor, and a person is not required to
delegated to me by the Administrator, 5 and spar web for cracks and damage (cracks respond to, nor shall a person be subject to
along the length of the bolt or broken bolt),
the FAA proposes to amend 14 CFR part a penalty for failure to comply with a
in accordance with the Accomplishment collection of information subject to the
39 as follows: Instructions of Airbus Service Bulletin A320– requirements of the Paperwork Reduction
57–1167, Revision 01, dated January 16, Act unless that collection of information
PART 39—AIRWORTHINESS 2018. If any crack or damage is found during
DIRECTIVES displays a current valid OMB Control
any inspection required by this paragraph, Number. The OMB Control Number for this
before further flight, obtain corrective actions information collection is 2120–0056. Public
■ 1. The authority citation for part 39 approved by the Manager, International reporting for this collection of information is
continues to read as follows: Section, Transport Standards Branch, FAA; estimated to be approximately 1 hour per
or the European Aviation Safety Agency response, including the time for reviewing
Authority: 49 U.S.C. 106(g), 40113, 44701. (EASA); or Airbus SAS’s EASA Design instructions, completing and reviewing the
Organization Approval (DOA); and collection of information. All responses to
§ 39.13 [Amended] accomplish the corrective actions within the this collection of information are mandatory.
■ 2. The FAA amends § 39.13 by adding compliance time specified therein. If Comments concerning the accuracy of this
the following new airworthiness approved by the DOA, the approval must burden and suggestions for reducing the
include the DOA-authorized signature. burden should be directed to the FAA at: 800
directive (AD): (2) If no cracks or damage are found during Independence Ave. SW, Washington, DC
Airbus SAS: Docket No. FAA–2018–0705; any inspection required by paragraph (h)(1) 20591, Attn: Information Collection
Product Identifier 2018–NM–077–AD. of this AD: Do a rotating probe test of the gear Clearance Officer, AES–200.
rib and spar web bolt holes for cracks and
(a) Comments Due Date damage (cracks in the bolt holes), in (k) Other FAA AD Provisions
We must receive comments by September accordance with the Accomplishment The following provisions also apply to this
24, 2018. Instructions of Airbus Service Bulletin A320– AD:
57–1167, Revision 01, dated January 16, (1) Alternative Methods of Compliance
(b) Affected ADs 2018. If any crack or damage is found during (AMOCs): The Manager, International
None. any inspection required by this paragraph, Section, Transport Standards Branch, FAA,
before further flight, obtain corrective actions has the authority to approve AMOCs for this
(c) Applicability
approved by the Manager, International AD, if requested using the procedures found
This AD applies to Airbus SAS Model Section, Transport Standards Branch, FAA; in 14 CFR 39.19. In accordance with 14 CFR
A321–111, –112, –131, –211, –212, –213, or EASA; or Airbus SAS’s EASA DOA; and 39.19, send your request to your principal
–231, and –232 airplanes, certificated in any accomplish the corrective actions within the inspector or local Flight Standards District
category, as identified in Airbus Service compliance time specified therein. If Office, as appropriate. If sending information
Bulletin A320–57–1167, Revision 01, dated approved by the DOA, the approval must directly to the International Section, send it
January 16, 2018. include the DOA authorized signature. to the attention of the person identified in
(3) If no cracks or damage are found during paragraph (l)(2) of this AD. Information may
(d) Subject any inspection required by paragraph (h)(2) be emailed to: 9-ANM-116-AMOC-
Air Transport Association (ATA) of of this AD: Ream the gear rib and the spar REQUESTS@faa.gov. Before using any
America Code 57, Wings. web bolt holes, in accordance with the approved AMOC, notify your appropriate
Accomplishment Instructions of Airbus principal inspector, or lacking a principal
(e) Reason
Service Bulletin A320–57–1167, Revision 01, inspector, the manager of the local flight
This AD was prompted by a report that dated January 16, 2018. If an oversize larger standards district office/certificate holding
during removal of left-hand (LH) gear rib 5, than 0.794 millimeter (0.0313 inch) is district office.
four failed fasteners (bolts attaching the gear required, before further flight, obtain (2) Contacting the Manufacturer: For any
rib to the wing inner rear spar) were corrective actions approved by the Manager, requirement in this AD to obtain corrective
discovered. We are issuing this AD to detect International Section, Transport Standards actions from a manufacturer, the action must
sradovich on DSK3GMQ082PROD with PROPOSALS
and correct cracked or failed (broken) Branch, FAA; or EASA; or Airbus SAS’s be accomplished using a method approved
fasteners (bolts) of the rib 5-to-rear spar EASA DOA; and accomplish the corrective by the Manager, International Section,
attachment, which could lead to reduced actions within the compliance time specified Transport Standards Branch, FAA; or the
structural integrity of the wing. therein. If approved by the DOA, the EASA; or Airbus SAS’s EASA DOA. If
approval must include the DOA authorized approved by the DOA, the approval must
(f) Compliance signature. include the DOA-authorized signature.
Comply with this AD within the (4) Replace any cracked or failed fasteners (3) Required for Compliance (RC): Except
compliance times specified, unless already (bolts) in accordance with the as required by paragraph (i) of this AD: If any
done. Accomplishment Instructions of Airbus service information contains procedures or
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![39380 Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules
tests that are identified as RC, those H2, Trent 1000–J2, Trent 1000–K2, and ECO Branch, FAA, 1200 District
procedures and tests must be done to comply Trent 1000–L2 turbofan engine models. Avenue, Burlington, MA 01803; phone:
with this AD; any procedures or tests that are This proposed AD was prompted by 781–238–7088; fax: 781–238–7199;
not identified as RC are recommended. Those reports of intermediate-pressure email: kevin.m.clark@faa.gov.
procedures and tests that are not identified
as RC may be deviated from using accepted
compressor (IPC) rotor seal failures. SUPPLEMENTARY INFORMATION:
methods in accordance with the operator’s This proposed AD would require initial
and repetitive on-wing borescope Comments Invited
maintenance or inspection program without
obtaining approval of an AMOC, provided inspections (BSI) of affected IPC rotor We invite you to send any written
the procedures and tests identified as RC can seals, and removing any cracked parts relevant data, views, or arguments about
be done and the airplane can be put back in from service. We are proposing this AD this proposal. Send your comments to
an airworthy condition. Any substitutions or to address the unsafe condition on these an address listed under the ADDRESSES
changes to procedures or tests identified as products. section. Include ‘‘Docket No. FAA–
RC require approval of an AMOC. 2018–0611; Product Identifier 2018–
DATES: We must receive comments on
(l) Related Information this proposed AD by September 24, NE–21–AD’’ at the beginning of your
(1) Refer to Mandatory Continuing 2018. comments. We specifically invite
Airworthiness Information (MCAI) EASA AD comments on the overall regulatory,
ADDRESSES: You may send comments,
2018–0102, dated April 27, 2018, for related economic, environmental, and energy
using the procedures found in 14 CFR
information. This MCAI may be found in the aspects of this NPRM. We will consider
AD docket on the internet at http:// 11.43 and 11.45, by any of the following
all comments received by the closing
www.regulations.gov by searching for and methods:
date and may amend this NPRM
locating Docket No. FAA–2018–0705. • Federal eRulemaking Portal: Go to
because of those comments.
(2) For more information about this AD, http://www.regulations.gov. Follow the
We will post all comments we
contact Sanjay Ralhan, Aerospace Engineer, instructions for submitting comments.
receive, without change, to http://
International Section, Transport Standards • Fax: 202–493–2251.
Branch, FAA, 2200 South 216th St., Des • Mail: U.S. Department of www.regulations.gov, including any
Moines, WA 98198; phone and fax: 206–231– Transportation, Docket Operations, M– personal information you provide. We
3223. 30, West Building Ground Floor, Room will also post a report summarizing each
(3) For service information identified in W12 140, 1200 New Jersey Avenue SE, substantive verbal contact we receive
this AD, contact Airbus SAS, Airworthiness about this NPRM.
Office—EAL, Rond-Point Emile Dewoitine
Washington, DC 20590.
No: 2, 31700 Blagnac Cedex, France; phone: • Hand Delivery: Deliver to Mail Discussion
+33 5 61 93 36 96; fax: +33 5 61 93 45 80; address above between 9 a.m. and 5
The European Aviation Safety Agency
email: airworthiness.A330-A340@airbus.com; p.m., Monday through Friday, except
(EASA), which is the Technical Agent
internet: http://www.airbus.com. You may Federal holidays.
for the Member States of the European
view this service information at the FAA, For service information identified in
Transport Standards Branch, 2200 South Community, has issued EASA AD 2018–
this NPRM, contact Rolls-Royce plc,
216th St., Des Moines, WA. For information 0095, dated April 24, 2018 (referred to
Corporate Communications, P.O. Box
on the availability of this material at the hereinafter as ‘‘the MCAI’’), to address
31, Derby, England, DE24 8BJ; phone:
FAA, call 206–231–3195. the unsafe condition on these products.
011–44–1332–242424; fax: 011–44–
Issued in Des Moines, Washington, on July The MCAI states:
1332–249936; email: corporate.care@
27, 2018. rolls-royce.com; internet: https:// During an engine shop visit, an affected
James Cashdollar, customers.rolls-royce.com/public/ seal was found with cracking at the seal
Acting Director, System Oversight Division, rollsroycecare. You may view this head. Propagation of such cracking may lead
Aircraft Certification Service. to failure, causing secondary impact damage
service information at the FAA, Engine to the IPC module.
[FR Doc. 2018–16733 Filed 8–8–18; 8:45 am] & Propeller Standards Branch, 1200 This condition, if not detected and
BILLING CODE 4910–13–P District Avenue, Burlington, MA 01803. corrected, could lead to engine power loss,
For information on the availability of possibly resulting in reduced control of the
this material at the FAA, call 781–238– aeroplane.
DEPARTMENT OF TRANSPORTATION 7759. To address this potential unsafe condition,
RR published the NMSB, providing
Federal Aviation Administration Examining the AD Docket instructions for on-wing borescope
You may examine the AD docket on inspections. RR previously issued NMSB
14 CFR Part 39 the internet at http:// TRENT 1000 72–J353, which contains
instructions for in-shop inspections.
[Docket No. FAA–2018–0611; Product
www.regulations.gov by searching for
For the reasons described above, this
Identifier 2018–NE–21–AD] and locating Docket No. FAA–2018– [EASA] AD requires repetitive borescope
0611; or in person at the Docket inspections of the front face of the affected
RIN 2120–AA64 Operations office between 9 a.m. and 5 seals and, depending on the findings,
p.m., Monday through Friday, except accomplishment of applicable corrections
Airworthiness Directives; Rolls-Royce Federal holidays. The AD docket action(s).
plc Turbofan Engines contains this NPRM, the mandatory You may obtain further information
AGENCY: Federal Aviation continuing airworthiness information by examining the MCAI in the AD
Administration (FAA), DOT. (MCAI), the regulatory evaluation, any docket on the internet at http://
sradovich on DSK3GMQ082PROD with PROPOSALS
ACTION: Notice of proposed rulemaking
comments received, and other www.regulations.gov by searching for
(NPRM). information. The address for Docket and locating Docket No. FAA–2018–
Operations (phone: 800–647–5527) is 0611.
SUMMARY: We propose to adopt a new listed above. Comments will be
airworthiness directive (AD) for all available in the AD docket shortly after Related Service Information Under 1
Rolls-Royce plc (RR) Trent 1000–A2, receipt. CFR Part 51
Trent 1000–C2, Trent 1000–D2, Trent FOR FURTHER INFORMATION CONTACT: We reviewed RR Non-Modification
1000–E2, Trent 1000–G2, Trent 1000– Kevin M. Clark, Aerospace Engineer, Service Bulletin (NMSB) Trent 1000 72–
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Document Created: 2018-08-09 01:11:49
Document Modified: 2018-08-09 01:11:49
| 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 24, 2018. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3223. | |
| FR Citation | 83 FR 39377 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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