80 FR 32063 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 108 (June 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 108 (June 5, 2015)
| Page Range | 32063-32066 | |
| FR Document | 2015-13342 |
[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)] [Proposed Rules] [Pages 32063-32066] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-13342] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1422; Directorate Identifier 2014-NM-125-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 98-18-26, for certain Airbus Model A320 series airplanes. AD 98-18-26 currently requires repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings; and repair, if necessary. Since we issued AD 98-18-26, we have received 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. This proposed AD would require 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, and a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, and repair if necessary. We are proposing 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: We must receive comments on this proposed AD by July 20, 2015. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. 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-2015- 1422; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, [[Page 32064]] except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647- 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1422; Directorate Identifier 2014-NM-125-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On August 28, 1998, we issued AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998). AD 98-18-26 requires repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe on certain Airbus Model A320 series airplanes. AD 98-18-26 contains a modification that provides a terminating action for the repetitive inspection requirements. Since we issued AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998), we have received 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 where shims were installed under the heads of 2 fasteners at the top end of the front spar vertical stringers using Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997, or on which modification 21290P1546 was accomplished during production. 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 by searching for and locating Docket No. FAA-2015- 1422. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-57-1178, Revision 01, 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. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 of this NPRM. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information Although EASA AD 2014-0069, dated March 19, 2014, specifies to accomplish an HFEC inspection for cracking of the vertical stiffeners radius, this proposed AD would require accomplishing an HFEC inspection for cracking of the radius of the front spar vertical stringers, since Airbus Service Bulletin A320-57-1178, Revision 01, Appendix 01, dated May 28, 2014, specifies the inspection is of the front spar vertical stringers. Costs of Compliance We estimate that this proposed AD affects 17 airplanes of U.S. registry. We also estimate that it would take about 24 work-hours per product to comply with the basic requirements of this proposed AD. The average labor [[Page 32065]] rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $34,680, or $2,040 per product. In addition, we estimate that any necessary follow-on actions would 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998), and adding the following new AD: Airbus: Docket No. FAA-2015-1422; Directorate Identifier 2014-NM- 125-AD. (a) Comments Due Date We must receive comments by July 20, 2015. (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 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, 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 manufacturer serial number (MSN) 0001 though 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: At the later of the times specified by paragraphs (h)(1)(i) through (h)(1)(iii) of this AD: (i) The later of the times specified by paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this AD: (A) Within 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) 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) 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 MSN 0001 to 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: 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 MSN 0001 to 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 [[Page 32066]] March 17, 1997: 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 MSN 0080 to 0155 inclusive: At the later of the times specified in paragraphs (h)(4)(i) or (h)(4)(ii) of this AD: (i) Before exceeding 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, 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 (1) 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. (2) 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 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. Issued in Renton, Washington, on May 18, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-13342 Filed 6-4-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32063
List of Subjects in 14 CFR Part 39 Precision Conversions LLC Service Bulletin requires repetitive inspections to detect
PC–757–11–0023, dated August 1, 2014. fatigue cracking of the front spar vertical
Air transportation, Aircraft, Aviation
safety, Incorporation by reference, (h) Alternative Methods of Compliance stringers on the wings; and repair, if
Safety. (AMOCs) necessary. Since we issued AD 98–18–
(1) The Manager, Seattle Aircraft 26, we have received reports that
The Proposed Amendment Certification Office (ACO), FAA, has the indicate new repetitive inspections
Accordingly, under the authority authority to approve AMOCs for this AD, if having new thresholds and intervals are
delegated to me by the Administrator, requested using the procedures found in 14 needed and that additional work is
the FAA proposes to amend 14 CFR part CFR 39.19. In accordance with 14 CFR 39.19, needed to accomplish the inspections
send your request to your principal inspector on airplanes on which a previous
39 as follows:
or local Flight Standards District Office, as modification has been accomplished.
appropriate. If sending information directly
PART 39—AIRWORTHINESS to the manager of the ACO, send it to the This proposed AD would require
DIRECTIVES attention of the person identified in repetitive high frequency eddy current
paragraph (i)(1) of this AD. Information may (HFEC) inspections for cracking of the
■ 1. The authority citation for part 39 be emailed to: 9-ANM-Seattle-ACO-AMOC- radius of the front spar vertical stringers
continues to read as follows: Requests@faa.gov. and the horizontal floor beam on frame
Authority: 49 U.S.C. 106(g), 40113, 44701. (2) Before using any approved AMOC, 36, and a rototest inspection for
notify your appropriate principal inspector, cracking of the fastener holes of the
§ 39.13 [Amended] or lacking a principal inspector, the manager front spar vertical stringers on frame 36,
■ 2. The FAA amends § 39.13 by adding of the local flight standards district office/
certificate holding district office. and repair if necessary. We are
the following new airworthiness proposing this AD to detect and correct
directive (AD): (i) Related Information fatigue cracking of the front spar vertical
The Boeing Company: Docket No. FAA– (1) For more information about this AD, stringers on the wings, which could
2015–1423; Directorate Identifier 2014– contact Narinder Luthra, Aerospace Engineer, result in the reduced structural integrity
NM–173–AD. Airframe Branch, ANM 120S, FAA, Seattle of the airframe.
Aircraft Certification Office (ACO), 1601 Lind
(a) Comments Due Date Avenue SW., Renton, WA 98057–3356; DATES: We must receive comments on
We must receive comments by July 20, phone: 425–917–6513; fax: 425–917–6590; this proposed AD by July 20, 2015.
2015. email: Narinder.Luthra@faa.gov. ADDRESSES: You may send comments by
(2) For service information identified in any of the following methods:
(b) Affected ADs this AD, contact Precision Conversions LLC, • Federal eRulemaking Portal: Go to
None. 4900 SW Griffith Drive, Suite 133, Beaverton, http://www.regulations.gov. Follow the
OR 97005; ATTN: Steven A. Lopez; phone:
(c) Applicability
503–601–3001; email: Steven.Lopez@
instructions for submitting comments.
This AD applies to The Boeing Company precisionaircraft.com. You may view this • Fax: 202–493–2251.
Model 757–200 series airplanes modified by referenced service information at the FAA, • Mail: U.S. Department of
the applicable supplemental type certificate Transport Airplane Directorate, 1601 Lind Transportation, Docket Operations, M–
identified in paragraphs (c)(1) and (c)(2) of Avenue SW., Renton, WA. For information 30, West Building Ground Floor, Room
this AD. on the availability of this material at the W12–140, 1200 New Jersey Avenue SE.,
(1) ST01529SE (http://rgl.faa.gov/ FAA, call 425–227–1221. Washington, DC 20590.
Regulatory_and_Guidance_Library/rgstc.nsf/
Issued in Renton, Washington, on May 18, • Hand Delivery: U.S. Department of
0/0AF09C3701A237EE86257A5D0064B3AA?
OpenDocument&Highlight=st01529se). 2015. Transportation, Docket Operations, M–
(2) ST02278SE (http://rgl.faa.gov/ John P. Piccola, Jr., 30, West Building Ground Floor, Room
Regulatory_and_Guidance_Library/rgstc.nsf/ Acting Manager, Transport Airplane W12–140, 1200 New Jersey Avenue SE.,
0/E54B5289A2E9F6EF86257B7F0056EDAF? Directorate, Aircraft Certification Service. Washington, DC, between 9 a.m. and 5
OpenDocument&Highlight=st02278se). [FR Doc. 2015–13358 Filed 6–4–15; 8:45 am] p.m., Monday through Friday, except
(d) Subject BILLING CODE 4910–13–P
Federal holidays.
For service information identified in
Air Transport Association (ATA) of
this proposed AD, contact Airbus,
America Code 11, Placards and Markings.
DEPARTMENT OF TRANSPORTATION Airworthiness Office—EIAS, 1 Rond
(e) Unsafe Condition Point Maurice Bellonte, 31707 Blagnac
This AD was prompted by reports of a Federal Aviation Administration Cedex, France; telephone +33 5 61 93 36
main cargo door being blown past its full 96; fax +33 5 61 93 44 51; email
open position while on the ground during 14 CFR Part 39 account.airworth-eas@airbus.com;
gusty wind conditions, which resulted in Internet http://www.airbus.com. You
uncontrolled fall down to its closed position. [Docket No. FAA–2015–1422; Directorate
Identifier 2014–NM–125–AD] may view this referenced service
We are issuing this AD to prevent damage to
information at the FAA, Transport
the main cargo door, which could result in RIN 2120–AA64
rapid decompression, leading to in-flight Airplane Directorate, 1601 Lind Avenue
breakup. SW., Renton, WA. For information on
Airworthiness Directives; Airbus the availability of this material at the
(f) Compliance Airplanes FAA, call 425–227–1221.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Comply with this AD within the AGENCY: Federal Aviation
compliance times specified, unless already Examining the AD Docket
Administration (FAA), DOT.
done. You may examine the AD docket on
ACTION: Notice of proposed rulemaking
(g) Installation (NPRM). the Internet at http://
Within 90 days after the effective date of
www.regulations.gov by searching for
this AD, install a new placard and bracket, SUMMARY: We propose to supersede and locating Docket No. FAA–2015–
replace the existing placard, and replace the Airworthiness Directive (AD) 98–18–26, 1422; or in person at the Docket
main cargo door control panel, in accordance for certain Airbus Model A320 series Management Facility between 9 a.m.
with the Accomplishment Instructions of airplanes. AD 98–18–26 currently and 5 p.m., Monday through Friday,
VerDate Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 E:\FR\FM\05JNP1.SGM 05JNP1](https://thefederalregister.org/doc/80_FR_32171/page/1.svg)
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except Federal holidays. The AD docket dated March 17, 1997, or on which 36 and repair if necessary], to be included in
contains this proposed AD, the modification 21290P1546 was Revision 01 of Airbus SB A320–57–1178, is
regulatory evaluation, any comments accomplished during production. required to accomplish the inspections. This
The European Aviation Safety Agency Final [EASA] AD has been amended
received, and other information. The
accordingly.
street address for the Docket Operations (EASA), which is the Technical Agent
office (telephone 800–647–5527) is in for the Member States of the European You may examine the MCAI in the AD
the ADDRESSES section. Comments will Union, has issued EASA Airworthiness docket on the Internet at http://
be available in the AD docket shortly Directive 2014–0069, dated March 19, www.regulations.gov by searching for
after receipt. 2014 (referred to after this as the and locating Docket No. FAA–2015–
FOR FURTHER INFORMATION CONTACT: Mandatory Continuing Airworthiness 1422.
Sanjay Ralhan, Aerospace Engineer, Information, or ‘‘the MCAI’’), to correct Related Service Information Under 1
International Branch, ANM–116, an unsafe condition on certain Airbus CFR Part 51
Transport Airplane Directorate, FAA, Model A320–211, –212, and –231
airplanes. The MCAI states: Airbus has issued Service Bulletin
1601 Lind Avenue SW., Renton, WA
A320–57–1178, Revision 01, including
98057–3356; telephone 425–227–1405; During center fuselage certification full
scale fatigue test, cracks were found on the Appendix 01, dated May 28, 2014. The
fax 425–227–1149.
front vertical stringer at frame 36. Analysis of service information describes
SUPPLEMENTARY INFORMATION: procedures for inspecting the radius of
these findings indicated that a number of in-
Comments Invited service aeroplanes could be similarly the front spar vertical stringers and the
affected. horizontal floor beam on frame 36 for
We invite you to send any written This condition, if not detected and cracking. The actions described in this
relevant data, views, or arguments about corrected, could lead to crack propagation service information are intended to
this proposed AD. Send your comments and consequent deterioration of the correct the unsafe condition identified
to an address listed under the structural integrity of the aeroplane.
To address this potential unsafe condition,
in the MCAI. This service information is
ADDRESSES section. Include ‘‘Docket No.
[Directorate General for Civil Aviation] reasonably available because the
FAA–2015–1422; Directorate Identifier interested parties have access to it
DGAC France AD 97–311–105 [which
2014–NM–125–AD’’ at the beginning of through their normal course of business
corresponds to FAA AD 98–18–26,
your comments. We specifically invite Amendment 39–10742 (63 FR 47423, or by the means identified in the
comments on the overall regulatory, September 8, 1998)] was issued to require ADDRESSES section of this NPRM.
economic, environmental, and energy repetitive [HFEC] inspections [for cracking]
aspects of this proposed AD. We will in accordance with the instruction of Airbus FAA’s Determination and Requirements
consider all comments received by the Service Bulletin (SB) A320–57–1016. At the of This Proposed AD
closing date and may amend this same time, the modification provided by This product has been approved by
proposed AD based on those comments. Airbus SB A320–57–1017 was considered to
be terminating action for the repetitive
the aviation authority of another
We will post all comments we country, and is approved for operation
inspections required by DGAC France AD
receive, without change, to http:// in the United States. Pursuant to our
97–311–105.
www.regulations.gov, including any Since that [DGAC] AD was issued, and bilateral agreement with the State of
personal information you provide. We following new analysis, modification per Design Authority, we have been notified
will also post a report summarizing each Airbus SB A320–57–1017 is no longer of the unsafe condition described in the
substantive verbal contact we receive considered to be terminating action for the MCAI and service information
about this proposed AD. repetitive inspections as required by DGAC referenced above. We are proposing this
France AD 97–311–105. AD because we evaluated all pertinent
Discussion Aeroplanes with [manufacturer serial
number] MSN 0080 up to 0155 inclusive
information and determined an unsafe
On August 28, 1998, we issued AD condition exists and is likely to exist or
98–18–26, Amendment 39–10742 (63 have been delivered with the addition of a 5
[millimeter] mm thick light alloy shim under develop on other products of the same
FR 47423, September 8, 1998). AD 98– type design.
the heads of 2 fasteners at the top end of the
18–26 requires repetitive inspections to front spar vertical stringers (Airbus
detect fatigue cracking of the front spar modification 21290P1546, which is the
Differences Between This Proposed AD
vertical stringers on the wings, which production line equivalent to in-service and the MCAI or Service Information
could result in the reduced structural modification through Airbus SB A320–57– Although EASA AD 2014–0069, dated
integrity of the airframe on certain 1017). From MSN 0156 and higher, all March 19, 2014, specifies to accomplish
Airbus Model A320 series airplanes. AD aeroplanes are delivered with vertical an HFEC inspection for cracking of the
98–18–26 contains a modification that stiffeners of the forward wing spar upper end
vertical stiffeners radius, this proposed
provides a terminating action for the with stiffener cap thickness increased from 4
to 6 mm (Airbus modification 21290P1547). AD would require accomplishing an
repetitive inspection requirements. HFEC inspection for cracking of the
Prompted by these findings, Airbus issued
Since we issued AD 98–18–26, SB A320–57–1178 to introduce new radius of the front spar vertical
Amendment 39–10742 (63 FR 47423, repetitive inspections with new thresholds stringers, since Airbus Service Bulletin
September 8, 1998), we have received and intervals. A320–57–1178, Revision 01, Appendix
reports that indicate new repetitive For the reasons described above, DGAC 01, dated May 28, 2014, specifies the
inspections having new thresholds and France AD 97–311–105 is superseded and inspection is of the front spar vertical
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
intervals are needed and that additional this [EASA] AD requires the repetitive stringers.
work is needed to accomplish the inspections at new thresholds and intervals.
inspections on airplanes where shims After EASA issued [proposed Costs of Compliance
airworthiness directive] PAD 14–021, it was
were installed under the heads of 2 We estimate that this proposed AD
discovered that additional work [HFEC
fasteners at the top end of the front spar inspections for cracking of the radius of spar affects 17 airplanes of U.S. registry.
vertical stringers using Airbus Service vertical stringers and horizontal beam in the We also estimate that it would take
Bulletin A320–57–1017, dated center fuselage of frame 36, and a rototest about 24 work-hours per product to
September 3, 1991; or Airbus Service inspection for cracking of the fastener holes comply with the basic requirements of
Bulletin A320–57–1017, Revision 01, of the spar vertical stringers radius on Frame this proposed AD. The average labor
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![Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32065
rate is $85 per work-hour. Based on The Proposed Amendment Repeat the inspections thereafter at the
these figures, we estimate the cost of compliance times specified in paragraphs
Accordingly, under the authority (g)(1) and (g)(2) of this AD.
this proposed AD on U.S. operators to delegated to me by the Administrator, (1) For Configuration 1 airplanes identified
be $34,680, or $2,040 per product. the FAA proposes to amend 14 CFR part in paragraph (h)(1) of this AD: At intervals
In addition, we estimate that any 39 as follows: not to exceed 8,800 flight cycles or 17,700
necessary follow-on actions would take flight hours, whichever occurs first.
about 49 work-hours and require parts PART 39—AIRWORTHINESS (2) For Configuration 2, 3, and 4 airplanes
costing $1,210, for a cost of $5,375 per DIRECTIVES identified in paragraphs (h)(2) through (h)(4)
product. We have no way of of this AD: At intervals not to exceed 24,900
determining the number of aircraft that ■ 1. The authority citation for part 39 flight cycles or 49,800 flight hours,
continues to read as follows: whichever occurs first.
might need this action.
Authority: 49 U.S.C. 106(g), 40113, 44701. (h) Compliance Times for Initial Inspections
Authority for This Rulemaking Required by Paragraph (g) of This AD
Title 49 of the United States Code § 39.13 [Amended] Do the initial inspections required by
specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by paragraph (g) of this AD within the
rules on aviation safety. Subtitle I, removing Airworthiness Directive (AD) applicable compliance times specified in
section 106, describes the authority of 98–18–26, Amendment 39–10742 (63 paragraphs (h)(1) through (h)(4) of this AD.
FR 47423, September 8, 1998), and (1) For Configuration 1 airplanes, having
the FAA Administrator. ‘‘Subtitle VII:
adding the following new AD: manufacturer serial number (MSN) 0001
Aviation Programs,’’ describes in more though MSN 0079 inclusive, on which the
detail the scope of the Agency’s Airbus: Docket No. FAA–2015–1422; modification specified by Airbus Service
authority. Directorate Identifier 2014–NM–125–AD. Bulletin A320–57–1017, dated September 3,
We are issuing this rulemaking under (a) Comments Due Date 1991; or Airbus Service Bulletin A320–57–
the authority described in ‘‘Subtitle VII, 1017, Revision 01, dated March 17, 1997, has
We must receive comments by July 20, not been accomplished: At the later of the
Part A, Subpart III, Section 44701: 2015.
General requirements.’’ Under that times specified by paragraphs (h)(1)(i)
(b) Affected ADs through (h)(1)(iii) of this AD:
section, Congress charges the FAA with (i) The later of the times specified by
promoting safe flight of civil aircraft in This AD replaces AD 98–18–26, paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this
air commerce by prescribing regulations Amendment 39–10742 (63 FR 47423, AD:
for practices, methods, and procedures September 8, 1998). (A) Within 24,000 flight cycles or 48,000
the Administrator finds necessary for (c) Applicability flight hours, whichever occurs first since
safety in air commerce. This regulation This AD applies to Airbus Model A320–
airplane first flight.
is within the scope of that authority (B) Within 60 days after the effective date
211, –212, and –231 airplanes, certificated in
because it addresses an unsafe condition of this AD.
any category, manufacturer serial numbers
that is likely to exist or develop on (ii) Within 8,800 flight cycles or 17,700
0001 through 0155 inclusive.
flight hours, whichever occurs first, since the
products identified in this rulemaking last inspection specified in Airbus Service
(d) Subject
action. Bulletin A320–57–1016 was accomplished.
Air Transport Association (ATA) of
Regulatory Findings America Code 57, Wings. (iii) Within 850 flight cycles or 1,700 flight
hours, whichever occurs first, after the
We determined that this proposed AD (e) Reason effective date of this AD, without exceeding
would not have federalism implications This AD was prompted by cracks found on 14,000 flight cycles after the last inspection
under Executive Order 13132. This the front vertical stringer at frame 36. This specified in Airbus Service Bulletin A320–
proposed AD would not have a AD was also prompted by reports that 57–1016 was accomplished.
indicate new repetitive inspections having (2) For Configuration 2 airplanes, having
substantial direct effect on the States, on
new thresholds and intervals are needed and MSN 0001 to 0079 inclusive, on which the
the relationship between the national actions specified by Airbus Service Bulletin
Government and the States, or on the that additional work is needed to accomplish
the inspections on airplanes on which a A320–57–1016, have not been done prior to
distribution of power and previous modification has been accomplishing the actions specified by
responsibilities among the various accomplished. We are issuing this AD to Airbus Service Bulletin A320–57–1017,
levels of government. detect and correct fatigue cracking of the dated September 3, 1991; or Airbus Service
For the reasons discussed above, I front spar vertical stringers on the wings, Bulletin A320–57–1017, Revision 01, dated
certify this proposed regulation: which could result in the reduced structural March 17, 1997: At the later of the times
integrity of the airframe. specified by paragraphs (h)(2)(i) and (h)(2)(ii)
1. Is not a ‘‘significant regulatory of this AD:
action’’ under Executive Order 12866; (f) Compliance (i) Within 8,800 flight cycles or 17,700
2. Is not a ‘‘significant rule’’ under the Comply with this AD within the flight hours, whichever occurs first, since the
DOT Regulatory Policies and Procedures compliance times specified, unless already modification specified in Airbus Service
(44 FR 11034, February 26, 1979); done. Bulletin A320–57–1017, dated September 3,
1991; or Airbus Service Bulletin A320–57–
3. Will not affect intrastate aviation in (g) Inspections 1017, Revision 01, dated December 6, 1995,
Alaska; and Within the applicable compliance times was accomplished.
4. Will not have a significant specified in paragraphs (h)(1) through (h)(4) (ii) Within 850 flight cycles or 1,700 flight
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
economic impact, positive or negative, of this AD, do a high frequency eddy current hours, whichever occurs first, after the
on a substantial number of small entities (HFEC) inspection for cracking of the radius effective date of this AD.
under the criteria of the Regulatory of the front spar vertical stringers and the (3) For Configuration 3 airplanes, having
Flexibility Act. horizontal floor beam on frame 36, and do a MSN 0001 to 0079 inclusive, on which the
rototest inspection for cracking of the actions specified by Airbus Service Bulletin
List of Subjects in 14 CFR Part 39 fastener holes of the front spar vertical A320–57–1016, have been done prior to
stringers on frame 36, in accordance with the accomplishing the actions specified by
Air transportation, Aircraft, Aviation Accomplishment Instructions of Airbus Airbus Service Bulletin A320–57–1017,
safety, Incorporation by reference, Service Bulletin A320–57–1178, Revision 01, dated September 3, 1991; or Airbus Service
Safety. including Appendix 01, dated May 28, 2014. Bulletin A320–57–1017, Revision 01, dated
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![32066 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules
March 17, 1997: At the later of the times searching for and locating Docket No. FAA– 11.43 and 11.45, by any of the following
specified by paragraphs (h)(3)(i) and (h)(3)(ii) 2015–1422. methods:
of this AD: (2) For service information identified in • Federal eRulemaking Portal: Go to
(i) Within 24,900 flight cycles or 49,800 this AD, contact Airbus, Airworthiness
flight hours, whichever occurs first, since the Office—EIAS, 1 Rond Point Maurice http://www.regulations.gov. Follow the
modification specified in Airbus Service Bellonte, 31707 Blagnac Cedex, France; instructions for submitting comments.
Bulletin A320–57–1017, dated September 3, telephone +33 5 61 93 36 96; fax +33 5 61 • Fax: 202–493–2251.
1991; or Airbus Service Bulletin A320–57– 93 44 51; email account.airworth-eas@ • Mail: U.S. Department of
1017, Revision 01, dated March 17, 1997, was airbus.com; Internet http://www.airbus.com. Transportation, Docket Operations,
accomplished. You may view this service information at the M–30, West Building Ground Floor,
(ii) Within 850 flight cycles or 1,700 flight FAA, Transport Airplane Directorate, 1601 Room W12–140, 1200 New Jersey
hours, whichever occurs first, after the Lind Avenue SW., Renton, WA. For
information on the availability of this
Avenue SE., Washington, DC 20590.
effective date of this AD.
(4) For Configuration 4 airplanes, having material at the FAA, call 425–227–1221. • Hand Delivery: Deliver to Mail
MSN 0080 to 0155 inclusive: address above between 9 a.m. and 5
Issued in Renton, Washington, on May 18,
At the later of the times specified in p.m., Monday through Friday, except
2015.
paragraphs (h)(4)(i) or (h)(4)(ii) of this AD: Federal holidays.
John P. Piccola, Jr.,
(i) Before exceeding 54,300 flight cycles or For service information identified in
108,600 flight hours, whichever occurs first Acting Manager, Transport Airplane this proposed AD, contact Aviation
since airplane first flight. Directorate, Aircraft Certification Service.
Partners Boeing, 2811 S. 102nd Street,
(ii) Within 60 days after the effective date [FR Doc. 2015–13342 Filed 6–4–15; 8:45 am] Suite 200, Seattle, WA 98168; telephone
of this AD. BILLING CODE 4910–13–P 206–762–1171; Internet https://
(i) Repair www.aviationpartnersboeing.com. You
If any crack is detected during any may view this referenced service
DEPARTMENT OF TRANSPORTATION
inspection required by paragraph (g) of this information at the FAA, Transport
AD: Before further flight, repair using a Airplane Directorate, 1601 Lind Avenue
method approved by the Manager,
Federal Aviation Administration
SW., Renton, WA. For information on
International Branch, ANM–116, Transport the availability of this material at the
Airplane Directorate, FAA; or the European 14 CFR Part 39
Aviation Safety Agency (EASA); or Airbus’s
FAA, call 425–227–1221.
[Docket No. FAA–2015–1421; Directorate
EASA Design Organization Approval (DOA). Identifier 2014–NM–177–AD] Examining the AD Docket
(j) Other FAA AD Provisions RIN 2120–AA64 You may examine the AD docket on
The following provisions also apply to this the Internet at http://
AD: Airworthiness Directives; The Boeing www.regulations.gov by searching for
(1) Alternative Methods of Compliance Company Airplanes and locating Docket No. FAA–2015–
(AMOCs): The Manager, International 1421; or in person at the Docket
Branch, ANM–116, FAA, has the authority to AGENCY: Federal Aviation
Administration (FAA), DOT. Management Facility between 9 a.m.
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. and 5 p.m., Monday through Friday,
ACTION: Notice of proposed rulemaking
In accordance with 14 CFR 39.19, send your except Federal holidays. The AD docket
(NPRM). contains this proposed AD, the
request to your principal inspector or local
Flight Standards District Office, as SUMMARY: We propose to adopt a new regulatory evaluation, any comments
appropriate. If sending information directly airworthiness directive (AD) for certain received, and other information. The
to the International Branch, send it to ATTN: The Boeing Company Model 767–300 street address for the Docket Office
Sanjay Ralhan, Aerospace Engineer, (phone: 800–647–5527) is in the
International Branch, ANM–116, Transport
and –300F series airplanes. This
proposed AD was prompted by reports ADDRESSES section. Comments will be
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; of fatigue cracking on airplanes with available in the AD docket shortly after
telephone 425–227–1405; fax 425–227–1149. Aviation Partners Boeing winglets receipt.
Information may be emailed to: 9-ANM-116- installed. This proposed AD would FOR FURTHER INFORMATION CONTACT:
AMOC-REQUESTS@faa.gov. Before using require a high frequency eddy current Allen Rauschendorfer, Aerospace
any approved AMOC, notify your appropriate (HFEC) inspection for cracking of the Engineer, Airframe Branch, ANM–120S,
principal inspector, or lacking a principal lower outboard wing skin, and repair or FAA, Seattle Aircraft Certification
inspector, the manager of the local flight modification if necessary. This
standards district office/certificate holding Office, 1601 Lind Avenue SW., Renton,
district office. The AMOC approval letter
proposed AD would also require one of WA 98057–3356; phone: 425–917–6487;
must specifically reference this AD. three follow-on actions: Repeating the fax: 425–917–6590; email:
(2) Contacting the Manufacturer: As of the HFEC inspections; modifying certain Allen.Rauschendorfer@faa.gov.
effective date of this AD, for any requirement internal stringers and oversizing and SUPPLEMENTARY INFORMATION:
in this AD to obtain corrective actions from plugging the existing fastener holes of
a manufacturer, the action must be the lower wing; or modifying the Comments Invited
accomplished using a method approved by external doubler/tripler and doing
the Manager, International Branch, ANM– We invite you to send any written
repetitive post-modification inspections. relevant data, views, or arguments about
116, Transport Airplane Directorate, FAA; or
We are proposing this AD to prevent this proposal. Send your comments to
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must fatigue cracking in the lower outboard an address listed under the ADDRESSES
include the DOA-authorized signature. wing skin, which could result in failure section. Include ‘‘Docket No. FAA–
and subsequent separation of the wing 2015–1421; Directorate Identifier 2014–
(k) Related Information
and winglet and consequent reduced NM–177–AD’’ at the beginning of your
(1) Refer to Mandatory Continuing controllability of the airplane.
Airworthiness Information (MCAI) EASA
comments. We specifically invite
DATES: We must receive comments on comments on the overall regulatory,
Airworthiness Directive 2014–0069, dated
March 19, 2014, for related information. This this proposed AD by July 20, 2015. economic, environmental, and energy
MCAI may be found in the AD docket on the ADDRESSES: You may send comments, aspects of this proposed AD. We will
Internet at http://www.regulations.gov by using the procedures found in 14 CFR consider all comments received by the
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Document Created: 2015-12-15 15:20:23
Document Modified: 2015-12-15 15:20:23
| 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 July 20, 2015. | |
| 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 | 80 FR 32063 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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