81 FR 3316 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 13 (January 21, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 13 (January 21, 2016)
| Page Range | 3316-3319 | |
| FR Document | 2016-00373 |
[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)] [Rules and Regulations] [Pages 3316-3319] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-00373] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1422; Directorate Identifier 2014-NM-125-AD; Amendment 39-18370; AD 2016-01-11] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 98-18-26, for certain Airbus Model A320 series airplanes. AD 98-18-26 required repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings; and repair, if necessary. This new AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, and repair if necessary. This AD was prompted by reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. We are issuing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe. DATES: This AD becomes effective February 25, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 25, 2016. ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1422; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket Number FAA- 2015-1422. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998). AD 98-18-26 applied to certain Airbus Model A320 series airplanes. The NPRM published in the Federal Register on June 5, 2015 (80 FR 32063). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0069, dated March 19, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Airbus Model A320-211, -212, and -231 airplanes. The MCAI states: During center fuselage certification full scale fatigue test, cracks were found on the front vertical stringer at frame 36. Analysis of these findings indicated that a number of in-service aeroplanes could be similarly affected. This condition, if not detected and corrected, could lead to crack propagation and consequent deterioration of the structural integrity of the aeroplane. To address this potential unsafe condition, [Directorate General for Civil Aviation] DGAC France AD 97-311-105 [which corresponds to FAA AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998)] was issued to require repetitive [HFEC] inspections [for cracking] in accordance with the instruction of Airbus Service Bulletin (SB) A320-57-1016. At the same time, the modification provided by Airbus SB A320-57-1017 was considered to be terminating action for the repetitive inspections required by DGAC France AD 97- 311-105. Since that [DGAC] AD was issued, and following new analysis, modification per Airbus SB A320-57-1017 is no longer considered to be terminating action for the repetitive inspections as required by DGAC France AD 97-311-105. Aeroplanes with [manufacturer serial number] MSN 0080 up to 0155 inclusive have been delivered with the addition of a 5 [millimeter] mm thick light alloy shim under the heads of 2 fasteners at the top end of the front spar vertical stringers (Airbus modification 21290P1546, which is the production line equivalent to in-service modification through Airbus SB A320-57-1017). From MSN 0156 and higher, all aeroplanes are delivered with vertical stiffeners of the forward wing spar upper end with stiffener cap thickness increased from 4 to 6 mm (Airbus modification 21290P1547). Prompted by these findings, Airbus issued SB A320-57-1178 to introduce new repetitive inspections with new thresholds and intervals. For the reasons described above, DGAC France AD 97-311-105 is superseded and this [EASA] AD requires the repetitive inspections at new thresholds and intervals. After EASA issued [proposed airworthiness directive] PAD 14-021, it was discovered that additional work [HFEC inspections for cracking of the radius of spar vertical stringers and horizontal beam in the center fuselage of frame 36, and a rototest inspection for cracking of the fastener holes of the spar vertical stringers radius on Frame 36 and repair if necessary], to be included in Revision 01 of Airbus SB A320-57-1178, is required to accomplish the inspections. This Final [EASA] AD has been amended accordingly. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-1422-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 32063, June 5, 2015) and the FAA's response to the comments. [[Page 3317]] Requests for Clarification of Certain Requirements Delta Airlines (DAL) asked that we move the repetitive inspection intervals from paragraph (g) of the proposed AD (80 FR 32063, June 5, 2015), and create a new paragraph (i) with the repetitive inspection intervals. DAL stated that having the inspection method and the repetitive inspection intervals in one paragraph, as well as a separate paragraph for the initial inspection is cumbersome. We do not agree with the requested changes. We re-examined the structure of the regulatory text of this AD, and have determined that the specified language as proposed is clear and aligns with the MCAI. Therefore, we have not changed this AD in this regard. DAL also asked that we add sub-steps to requirements in the proposed AD (80 FR 32063, June 5, 2015), to clarify the inspection requirements specified in Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014. We do not agree. Our goal in referring to the Accomplishment Instructions of the service information is to ensure that operators follow the details in the inspection steps shown therein. DAL has the option of creating task cards if it makes accomplishing the sub-steps easier, provided the cards meet the intent of the AD. We have not changed this AD in this regard. Additionally, DAL asked that Appendix 01 of Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, be removed from the service bulletin identification in the NPRM (80 FR 32063, June 5, 2015), because Appendix 01 has Gantt Chart information that should not be highlighted as a regulatory requirement for compliance. We do not agree. The information in Appendix 01 of Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, may be helpful to operators that want to determine the number of work hours necessary to accomplish specific actions. Moreover, Appendix 01 does not contain a requirement for compliance. We have not changed this AD in this regard. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed, with minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 32063, June 5, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 32063, June 5, 2015). We have also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014. The service information describes procedures for inspecting the radius of the front spar vertical stringers and the horizontal floor beam on frame 36 for cracking. 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 17 airplanes of U.S. registry. We also estimate that it will take about 24 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 $34,680, or $2,040 per product. In addition, we estimate that any necessary follow-on actions will take about 49 work-hours and require parts costing $1,210, for a cost of $5,375 per product. We have no way of determining the number of aircraft that might need this action. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We 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. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-1422; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647- 5527) is in the ADDRESSES section. 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) 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998), and adding the following new AD: 2016-01-11 Airbus: Amendment 39-18370. Docket No. FAA-2015-1422; Directorate Identifier 2014-NM-125-AD. [[Page 3318]] (a) Effective Date This AD becomes effective February 25, 2016. (b) Affected ADs This AD replaces AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998). (c) Applicability This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers (MSN) 0001 through 0155 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by cracks found on the front vertical stringer at frame 36. This AD was also prompted by reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. We are issuing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections Within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, and do a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014. Repeat the inspections thereafter at the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD. (1) For Configuration 1 airplanes identified in paragraph (h)(1) of this AD: At intervals not to exceed 8,800 flight cycles or 17,700 flight hours, whichever occurs first. (2) For Configuration 2, 3, and 4 airplanes identified in paragraphs (h)(2) through (h)(4) of this AD: At intervals not to exceed 24,900 flight cycles or 49,800 flight hours, whichever occurs first. (h) Compliance Times for Initial Inspections Required by Paragraph (g) of This AD Do the initial inspections required by paragraph (g) of this AD within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD. (1) For Configuration 1 airplanes, having MSNs 0001 through MSN 0079 inclusive, on which the modification specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997, has not been accomplished: Inspect at the later of the times specified by paragraphs (h)(1)(i) through (h)(1)(iii) of this AD. (i) Inspect at the later of the times specified by paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this AD. (A) Prior to the accumulation of 24,000 flight cycles or 48,000 flight hours, whichever occurs first since airplane first flight. (B) Within 60 days after the effective date of this AD. (ii) Inspect within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the last inspection specified in Airbus Service Bulletin A320-57-1016 was accomplished. (iii) Inspect within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD, without exceeding 14,000 flight cycles after the last inspection specified in Airbus Service Bulletin A320-57-1016 was accomplished. (2) For Configuration 2 airplanes, having MSNs 0001 through 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320-57-1016, have not been done prior to accomplishing the actions specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997: Inspect at the later of the times specified by paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) Within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated December 6, 1995, was accomplished. (ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD. (3) For Configuration 3 airplanes, having MSNs 0001 through 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320-57-1016, have been done prior to accomplishing the actions specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997: Inspect at the later of the times specified by paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. (i) Within 24,900 flight cycles or 49,800 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997, was accomplished. (ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD. (4) For Configuration 4 airplanes, having MSNs 0080 through 0155 inclusive: Inspect at the later of the times specified in paragraphs (h)(4)(i) or (h)(4)(ii) of this AD. (i) Prior to the accumulation of 54,300 flight cycles or 108,600 flight hours, whichever occurs first since airplane first flight. (ii) Within 60 days after the effective date of this AD. (i) Repair If any crack is detected during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. 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. The AMOC approval letter must specifically reference 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0069, dated March 19, 2014, 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-2015-1422. (l) 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. (3) The following service information was approved for IBR on February 25, 2016. (i) Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014. (ii) Reserved. (4) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice [[Page 3319]] Bellonte, 31707 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. (5) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (6) 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 Renton, Washington, on December 31, 2015. Philip Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-00373 Filed 1-20-16; 8:45 am] BILLING CODE 4910-13-P
![3316 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations
telephone +44(0)2890–462469; fax reduced structural integrity of the these findings indicated that a number of in-
+44(0)2890 468444; email airframe. service aeroplanes could be similarly
michael.mulholland@aero.bombardier.com; affected.
Internet http://www.bombardier.com. DATES: This AD becomes effective This condition, if not detected and
(5) You may view this service information February 25, 2016. corrected, could lead to crack propagation
at the FAA, Transport Airplane Directorate, The Director of the Federal Register and consequent deterioration of the
1601 Lind Avenue SW., Renton, WA. For approved the incorporation by reference structural integrity of the aeroplane.
information on the availability of this of a certain publication listed in this AD To address this potential unsafe condition,
material at the FAA, call 425–227–1221. as of February 25, 2016. [Directorate General for Civil Aviation]
(6) You may view this service information DGAC France AD 97–311–105 [which
ADDRESSES: You may examine the AD
that is incorporated by reference at the corresponds to FAA AD 98–18–26,
docket on the Internet at http:// Amendment 39–10742 (63 FR 47423,
National Archives and Records
Administration (NARA). For information on
www.regulations.gov/ September 8, 1998)] was issued to require
the availability of this material at NARA, call #!docketDetail;D=FAA-2015-1422; or in repetitive [HFEC] inspections [for cracking]
202–741–6030, or go to: http:// person at the Docket Management in accordance with the instruction of Airbus
www.archives.gov/federal-register/cfr/ibr- Facility, U.S. Department of Service Bulletin (SB) A320–57–1016. At the
locations.html. Transportation, Docket Operations, M– same time, the modification provided by
30, West Building Ground Floor, Room Airbus SB A320–57–1017 was considered to
Issued in Renton, Washington, on January be terminating action for the repetitive
4, 2016. W12–140, 1200 New Jersey Avenue SE., inspections required by DGAC France AD
Victor Wicklund, Washington, DC. 97–311–105.
For service information identified in Since that [DGAC] AD was issued, and
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
this AD, contact Airbus, Airworthiness following new analysis, modification per
Office—EIAS, 1 Rond Point Maurice Airbus SB A320–57–1017 is no longer
[FR Doc. 2016–00378 Filed 1–20–16; 8:45 am]
Bellonte, 31707 Blagnac Cedex, France; considered to be terminating action for the
BILLING CODE 4910–13–P repetitive inspections as required by DGAC
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth- France AD 97–311–105.
eas@airbus.com; Internet http:// Aeroplanes with [manufacturer serial
DEPARTMENT OF TRANSPORTATION number] MSN 0080 up to 0155 inclusive
www.airbus.com. You may view this have been delivered with the addition of a 5
Federal Aviation Administration referenced service information at the [millimeter] mm thick light alloy shim under
FAA, Transport Airplane Directorate, the heads of 2 fasteners at the top end of the
14 CFR Part 39 1601 Lind Avenue SW., Renton, WA. front spar vertical stringers (Airbus
For information on the availability of modification 21290P1546, which is the
[Docket No. FAA–2015–1422; Directorate this material at the FAA, call 425–227– production line equivalent to in-service
Identifier 2014–NM–125–AD; Amendment modification through Airbus SB A320–57–
1221. It is also available on the Internet
39–18370; AD 2016–01–11] 1017). From MSN 0156 and higher, all
at http://www.regulations.gov by
aeroplanes are delivered with vertical
RIN 2120–AA64 searching for and locating Docket stiffeners of the forward wing spar upper end
Number FAA–2015–1422. with stiffener cap thickness increased from 4
Airworthiness Directives; Airbus FOR FURTHER INFORMATION CONTACT: to 6 mm (Airbus modification 21290P1547).
Airplanes Sanjay Ralhan, Aerospace Engineer, Prompted by these findings, Airbus issued
AGENCY: Federal Aviation International Branch, ANM–116, SB A320–57–1178 to introduce new
Administration (FAA), Department of Transport Airplane Directorate, FAA, repetitive inspections with new thresholds
1601 Lind Avenue SW., Renton, WA and intervals.
Transportation (DOT). For the reasons described above, DGAC
ACTION: Final rule. 98057–3356; telephone 425–227–1405; France AD 97–311–105 is superseded and
fax 425–227–1149. this [EASA] AD requires the repetitive
SUMMARY: We are superseding SUPPLEMENTARY INFORMATION: inspections at new thresholds and intervals.
Airworthiness Directive (AD) 98–18–26, After EASA issued [proposed
for certain Airbus Model A320 series Discussion airworthiness directive] PAD 14–021, it was
airplanes. AD 98–18–26 required We issued a notice of proposed discovered that additional work [HFEC
repetitive inspections to detect fatigue rulemaking (NPRM) to amend 14 CFR inspections for cracking of the radius of spar
cracking of the front spar vertical part 39 to supersede AD 98–18–26, vertical stringers and horizontal beam in the
stringers on the wings; and repair, if center fuselage of frame 36, and a rototest
Amendment 39–10742 (63 FR 47423,
inspection for cracking of the fastener holes
necessary. This new AD requires September 8, 1998). AD 98–18–26 of the spar vertical stringers radius on Frame
repetitive high frequency eddy current applied to certain Airbus Model A320 36 and repair if necessary], to be included in
(HFEC) inspections for cracking of the series airplanes. The NPRM published Revision 01 of Airbus SB A320–57–1178, is
radius of the front spar vertical stringers in the Federal Register on June 5, 2015 required to accomplish the inspections. This
and the horizontal floor beam on frame (80 FR 32063). Final [EASA] AD has been amended
36, a rototest inspection for cracking of The European Aviation Safety Agency accordingly.
the fastener holes of the front spar (EASA), which is the Technical Agent You may examine the MCAI in the
vertical stringers on frame 36, and repair for the Member States of the European AD docket on the Internet at http://
if necessary. This AD was prompted by Union, has issued EASA Airworthiness www.regulations.gov/
reports that indicate new repetitive Directive 2014–0069, dated March 19, #!documentDetail;D=FAA-2015-1422-
inspections having new thresholds and 2014 (referred to after this as the 0002.
intervals are needed and that additional Mandatory Continuing Airworthiness
jstallworth on DSK7TPTVN1PROD with RULES
work is needed to accomplish the Information, or ‘‘the MCAI’’), to correct Comments
inspections on airplanes on which a an unsafe condition on certain Airbus We gave the public the opportunity to
previous modification has been Model A320–211, –212, and –231 participate in developing this AD. The
accomplished. We are issuing this AD to airplanes. The MCAI states: following presents the comments
detect and correct fatigue cracking of the During center fuselage certification full received on the NPRM (80 FR 32063,
front spar vertical stringers on the scale fatigue test, cracks were found on the June 5, 2015) and the FAA’s response to
wings, which could result in the front vertical stringer at frame 36. Analysis of the comments.
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![Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3317
Requests for Clarification of Certain • Do not add any additional burden Regulatory Findings
Requirements upon the public than was already
We determined that this AD will not
Delta Airlines (DAL) asked that we proposed in the NPRM (80 FR 32063,
have federalism implications under
move the repetitive inspection intervals June 5, 2015).
Executive Order 13132. This AD will
from paragraph (g) of the proposed AD We have also determined that these not have a substantial direct effect on
(80 FR 32063, June 5, 2015), and create changes will not increase the economic the States, on the relationship between
a new paragraph (i) with the repetitive burden on any operator or increase the the national government and the States,
inspection intervals. DAL stated that scope of this AD. or on the distribution of power and
having the inspection method and the Related Service Information Under 1 responsibilities among the various
repetitive inspection intervals in one CFR Part 51 levels of government.
paragraph, as well as a separate For the reasons discussed above, I
paragraph for the initial inspection is Airbus has issued Service Bulletin
A320–57–1178, Revision 01, dated May certify that this AD:
cumbersome. 1. Is not a ‘‘significant regulatory
We do not agree with the requested 28, 2014, including Appendix 01, dated
May 28, 2014. The service information action’’ under Executive Order 12866;
changes. We re-examined the structure 2. Is not a ‘‘significant rule’’ under the
of the regulatory text of this AD, and describes procedures for inspecting the
radius of the front spar vertical stringers DOT Regulatory Policies and Procedures
have determined that the specified (44 FR 11034, February 26, 1979);
language as proposed is clear and aligns and the horizontal floor beam on frame
36 for cracking. This service information 3. Will not affect intrastate aviation in
with the MCAI. Therefore, we have not
is reasonably available because the Alaska; and
changed this AD in this regard.
DAL also asked that we add sub-steps interested parties have access to it 4. Will not have a significant
to requirements in the proposed AD (80 through their normal course of business economic impact, positive or negative,
FR 32063, June 5, 2015), to clarify the or by the means identified in the on a substantial number of small entities
inspection requirements specified in ADDRESSES section. under the criteria of the Regulatory
Airbus Service Bulletin A320–57–1178, Flexibility Act.
Costs of Compliance
Revision 01, dated May 28, 2014. Examining the AD Docket
We do not agree. Our goal in referring We estimate that this AD affects 17
to the Accomplishment Instructions of airplanes of U.S. registry. You may examine the AD docket on
the service information is to ensure that We also estimate that it will take the Internet at http://
operators follow the details in the about 24 work-hours per product to www.regulations.gov/#!docket
inspection steps shown therein. DAL comply with the basic requirements of Detail;D=FAA-2015-1422; or in person
has the option of creating task cards if this AD. The average labor rate is $85 at the Docket Management Facility
it makes accomplishing the sub-steps per work-hour. Based on these figures, between 9 a.m. and 5 p.m., Monday
easier, provided the cards meet the we estimate the cost of this AD on U.S. through Friday, except Federal holidays.
intent of the AD. We have not changed operators to be $34,680, or $2,040 per The AD docket contains this AD, the
this AD in this regard. product. regulatory evaluation, any comments
Additionally, DAL asked that In addition, we estimate that any received, and other information. The
Appendix 01 of Airbus Service Bulletin necessary follow-on actions will take street address for the Docket Operations
A320–57–1178, Revision 01, dated May about 49 work-hours and require parts office (telephone 800–647–5527) is in
28, 2014, be removed from the service costing $1,210, for a cost of $5,375 per the ADDRESSES section.
bulletin identification in the NPRM (80 product. We have no way of List of Subjects in 14 CFR Part 39
FR 32063, June 5, 2015), because determining the number of aircraft that
Appendix 01 has Gantt Chart might need this action. Air transportation, Aircraft, Aviation
information that should not be safety, Incorporation by reference,
Authority for This Rulemaking Safety.
highlighted as a regulatory requirement
for compliance. Title 49 of the United States Code Adoption of the Amendment
We do not agree. The information in specifies the FAA’s authority to issue
Appendix 01 of Airbus Service Bulletin rules on aviation safety. Subtitle I, Accordingly, under the authority
A320–57–1178, Revision 01, dated May section 106, describes the authority of delegated to me by the Administrator,
28, 2014, may be helpful to operators the FAA Administrator. ‘‘Subtitle VII: the FAA amends 14 CFR part 39 as
that want to determine the number of Aviation Programs,’’ describes in more follows:
work hours necessary to accomplish detail the scope of the Agency’s
authority. PART 39—AIRWORTHINESS
specific actions. Moreover, Appendix 01
We are issuing this rulemaking under DIRECTIVES
does not contain a requirement for
compliance. We have not changed this the authority described in ‘‘Subtitle VII,
■ 1. The authority citation for part 39
AD in this regard. Part A, Subpart III, Section 44701:
continues to read as follows:
General requirements.’’ Under that
Conclusion section, Congress charges the FAA with Authority: 49 U.S.C. 106(g), 40113, 44701.
We reviewed the relevant data and promoting safe flight of civil aircraft in § 39.13 [Amended]
determined that air safety and the air commerce by prescribing regulations
public interest require adopting this AD for practices, methods, and procedures ■ 2. The FAA amends § 39.13 by
jstallworth on DSK7TPTVN1PROD with RULES
as proposed, with minor editorial the Administrator finds necessary for removing Airworthiness Directive (AD)
changes. We have determined that these safety in air commerce. This regulation 98–18–26, Amendment 39–10742 (63
minor changes: is within the scope of that authority FR 47423, September 8, 1998), and
• Are consistent with the intent that because it addresses an unsafe condition adding the following new AD:
was proposed in the NPRM (80 FR that is likely to exist or develop on 2016–01–11 Airbus: Amendment 39–18370.
32063, June 5, 2015) for correcting the products identified in this rulemaking Docket No. FAA–2015–1422; Directorate
unsafe condition; and action. Identifier 2014–NM–125–AD.
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![Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3319
Bellonte, 31707 Blagnac Cedex, France; www.mdhelicopters.com. You may Comments
telephone +33 5 61 93 36 96; fax +33 5 61 review a copy of the referenced service
93 44 51; email account.airworth-eas@ We gave the public the opportunity to
information at the FAA, Office of the participate in developing this AD, but
airbus.com; Internet http://www.airbus.com.
Regional Counsel, Southwest Region, we received no comments on the NPRM
(5) You may view this service information
at the FAA, Transport Airplane Directorate, 10101 Hillwood Pkwy, Room 6N–321, (80 FR 32508, June 9, 2015).
1601 Lind Avenue SW., Renton, WA. For Fort Worth, TX 76177.
information on the availability of this FAA’s Determination
Examining the AD Docket
material at the FAA, call 425–227–1221. We have reviewed the relevant
(6) You may view this service information You may examine the AD docket on
that is incorporated by reference at the information and determined that an
the Internet at http:// unsafe condition exists and is likely to
National Archives and Records
www.regulations.gov by searching for exist or develop on other products of
Administration (NARA). For information on
the availability of this material at NARA, call and locating Docket No. FAA–2015– these same type designs and that air
202–741–6030, or go to: http:// 1998; or in person at the Docket safety and the public interest require
www.archives.gov/federal-register/cfr/ibr- Operations Office between 9 a.m. and 5 adopting the AD requirements as
locations.html. p.m., Monday through Friday, except proposed.
Issued in Renton, Washington, on Federal holidays. The AD docket
December 31, 2015. contains this AD, the economic Related Service Information
Philip Forde, evaluation, any comments received, and MDHI issued Service Bulletin
Acting Manager, Transport Airplane other information. The street address for SB500N–046 and SB600N–054 (SB) as a
Directorate, Aircraft Certification Service. the Docket Operations Office (phone: single bulletin on July 9, 2012. The SB
[FR Doc. 2016–00373 Filed 1–20–16; 8:45 am]
800–647–5527) is U.S. Department of calls for a one-time inspection within
Transportation, Docket Operations 100 flight hours to determine the
BILLING CODE 4910–13–P
Office, M–30, West Building Ground rotating cone assembly’s part number on
Floor, Room W12–140, 1200 New Jersey MDHI Model 500N and 600N
DEPARTMENT OF TRANSPORTATION Avenue SE., Washington, DC 20590. helicopters. The SB then states the need
FOR FURTHER INFORMATION CONTACT: to correct the component record for
Federal Aviation Administration Galib Abumeri, Aerospace Engineer, Los certain rotating cone assemblies.
Angeles Aircraft Certification Office, The SB also specifies determining the
14 CFR Part 39 Transport Airplane Directorate, FAA, rotating cone assembly’s total service
[Docket No. FAA–2015–1998; Directorate 3960 Paramount Blvd., Lakewood, time since new and recording this on
Identifier 2014–SW–035–AD; Amendment California 90712, telephone 562–627– the component record. MDHI reports
39–18379; AD 2016–01–19] 5324; email Galib.Abumeri@faa.gov. that failure to comply with the SB may
result in an aircraft exceeding the life
RIN 2120–AA64 SUPPLEMENTARY INFORMATION:
limit of the rotating cone assembly and
Airworthiness Directives; MD Discussion that this could lead to component
Helicopters Inc. failure and loss of directional control of
On June 9, 2015, at 80 FR 32508, the the helicopter.
AGENCY: Federal Aviation Federal Register published our notice of
Administration (FAA), DOT. proposed rulemaking (NPRM), which Differences Between This AD and the
ACTION: Final rule. proposed to amend 14 CFR part 39 by Service Information
adding an AD that would apply to The SB calls for inspecting the
SUMMARY: We are adopting a new MDHI Model 500N helicopters with a rotating cone assembly to determine its
airworthiness directive (AD) for MD rotating cone assembly part number (P/ P/N. We make no requirement about
Helicopters Inc. (MDHI) Model 500N N) 500N3740–81 installed, and Model how to determine the P/N. The
and 600N helicopters with certain 600N helicopters with a rotating cone compliance time for the SB is within
rotating cone assemblies installed. This assembly P/N 500N3740–71 installed. 100 flight hours, while this AD requires
AD requires establishing a life limit of The NPRM proposed to require compliance within 1 year or by the next
10,000 hours time-in-service (TIS) on establishing a life limit of 10,000 hours annual inspection, whichever comes
these rotating cone assemblies. This AD TIS on these rotating cone assemblies. later.
was prompted by the determination that Although these parts have a life limit of
MDHI created rotating cone assemblies 10,000 hours TIS, they were incorrectly Costs of Compliance
with new dash numbers but incorrectly omitted from the Airworthiness We estimate that this AD affects 8
failed to identify them as life-limited Limitation Section of the Rotorcraft helicopters of U.S. Registry and that
parts. The actions are intended to Maintenance Manual. Some of the labor costs average $85 a work hour. We
prevent operation of rotating cone affected parts were sold as spares, while estimate that creating a component
assemblies past their life limits, failure others were installed on new helicopters history card and revising the
of the rotating cone assemblies, loss of in production. The proposed appropriate records takes 1 work-hour.
directional control, and subsequent loss requirements were intended to prevent No parts are needed for a total cost of
of control of the helicopter. operation of rotating cone assemblies $85 per helicopter and $680 for the U.S.
DATES: This AD is effective February 25, past their life limits, failure of the fleet.
2016. rotating cone assemblies, loss of
Authority for This Rulemaking
jstallworth on DSK7TPTVN1PROD with RULES
ADDRESSES: For service information directional control, and subsequent loss
identified in this final rule, contact MD of control of the helicopter. Title 49 of the United States Code
Helicopters, Inc., Attn: Customer Since the NPRM was issued, the FAA specifies the FAA’s authority to issue
Support Division, 4555 E. McDowell Southwest Regional Office has rules on aviation safety. Subtitle I,
Rd., Mail Stop M615, Mesa, AZ 85215– relocated. This AD includes the current section 106, describes the authority of
9734; telephone 1–800–388–3378; fax physical address of the FAA Southwest the FAA Administrator. Subtitle VII:
480–346–6813; or at http:// Regional Office. Aviation Programs, describes in more
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Document Created: 2018-02-02 12:33:28
Document Modified: 2018-02-02 12:33:28
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective February 25, 2016. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 81 FR 3316 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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