80 FR 74058 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 228 (November 27, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 228 (November 27, 2015)
| Page Range | 74058-74061 | |
| FR Document | 2015-30006 |
[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)] [Proposed Rules] [Pages 74058-74061] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-30006] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-5811; Directorate Identifier 2014-NM-158-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) 2004-19- 11 for certain Airbus Model 320 series airplanes. AD 2004-19-11 currently requires modification of the inner rear spar web of the wing, cold expansion of the attachment holes of the forward pintle fitting and the actuating cylinder anchorage of the main landing gear (MLG), repetitive ultrasonic inspections for cracking of the rear spar of the wing, and corrective action if necessary. AD 2004-19-11 also provides optional terminating action for the repetitive inspections. Since we issued AD 2004-19-11, we have determined that the terminating action is necessary to address the unsafe condition. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would retain the requirements of AD 2004-19-11 and would require the previously optional terminating action. We are proposing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the MLG. DATES: We must receive comments on this proposed AD by January 11, 2016. 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- 5811; 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 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 ADDRESSESsection. 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-2015-5811; Directorate Identifier 2014-NM-158-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 September 21, 2004, we issued AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004). AD 2004-19-11 requires actions intended to address an unsafe condition on certain Airbus Model 320 series airplanes. AD 2004-19-11 superseded AD 2000-10-15, Amendment 39-17739 (65 FR 34069, May 26, 2000). Since we issued AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), we have determined that the modification of the inner rear spar that is an optional terminating action of AD 2004-19-11 must be accomplished in order to address the identified unsafe condition. As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs have been developed to support initiatives that will ensure the continued airworthiness of aging airplane structure. The last element of those initiatives is the requirement to establish a limit of validity (LOV) of the engineering data that support the structural maintenance program under 14 CFR 26.21. This proposed AD is the result of an assessment of the previously established programs by the design approval holder (DAH). The actions specified in this proposed AD are necessary to complete certain programs to ensure the continued airworthiness of aging airplane structure and to support an airplane reaching its LOV. The European Aviation Safety Agency, which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0169, corrected July 22, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Airbus Model A320 series airplanes. The MCAI states: During centre fuselage certification full scale fatigue test, cracks were found on the [[Page 74059]] inner rear spar at holes position 52 on the right hand wing due to fatigue aspects. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To prevent such cracks, Airbus developed modifications, which were introduced in production and in service through several Airbus Service Bulletins (SB). DGAC France issued * * * [an earlier AD], which was subsequently superseded by [DGAC] AD 2001-249 [which corresponds with FAA AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004)], to require modification of the rear spar on some aeroplanes, post-modification repetitive inspections and, depending on findings, accomplishment of a repair. DGAC France AD 2001-249 also specified that modification in accordance with Airbus SB A320- 57-1089 (in-service equivalent to Airbus mod 24591) constituted (optional) terminating action for the repetitive inspections. Since that [DGAC] AD [2001-249] was issued, in the framework of the A320 Extended Service Goal (ESG), it has been determined that Airbus mod 24591 is necessary to allow aeroplanes to operate up to the new ESG limit. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 2001-249, which is superseded, and requires modification of all pre-mod 24591 aeroplanes. The modification includes modifying all specified fastener holes in the inner rear spar of the wing. 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-2015-5811. Related Service Information Under 1 CFR part 51 Airbus has issued the following service information. Airbus Service Bulletin A320-57-1004, Revision 02, dated June 14, 1993. This service information describes procedures for modifying the inner rear spar web of the wing. Airbus Service Bulletin A320-57-1060, Revision 2, dated December 16, 1994. This service information describes procedures for a cold expansion of all the attachment holes for the forward pintle fitting of the main landing gear (MLG), except for the holes that are for taper-lok bolts; and for a cold expansion of the holes at the actuating cylinder anchorage of the MLG. Airbus Mandatory Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001. This service information describes procedures for doing ultrasonic inspections for cracking of the rear spar of the wing. Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001. This service information describes modification of the airplane by accomplishing cold reexpansion of the holes in the inner rear spar for the attachment of gear rib 5, forward pintle fitting, and actuating cylinder anchorage; and the installation of interference fit fasteners in the rear spar and gear rib 5. 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 ADDRESSESsection 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. Costs of Compliance We estimate that this proposed AD affects 84 airplanes of U.S. registry. The actions required by AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), and retained in this proposed AD take about 684 work-hours per product, at an average labor rate of $85 per work- hour. Required parts cost about $13,644 per product. Based on these figures, the estimated cost of the actions that are required by AD 2004-19-11 is $71,784 per product. We also estimate that it would take about 980 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $32,727 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $9,746,268, or $116,027 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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) 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), and adding the following new AD: Airbus: Docket No. FAA-2015-5811; Directorate Identifier 2014-NM- 158-AD. (a) Comments Due Date We must receive comments by January 11, 2016. [[Page 74060]] (b) Affected ADs This AD replaces AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2014). (c) Applicability This AD applies to Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus modification (mod) 24591 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of fatigue cracking of the inner rear spar of the wing and also by the determination that the modification of the inner rear spar is necessary to address the unsafe condition. We are issuing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the main landing gear (MLG). (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification of Inner Rear Spar Web of the Wing, With Change to Acceptable Service Information This paragraph restates the requirements of paragraph (a) of AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), with a change to acceptable service information. For airplanes having manufacturer's serial numbers (MSNs) 003 through 008 inclusive, and 010 through 021 inclusive, except airplanes modified as specified in Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001: Prior to the accumulation of 12,000 total flight cycles, or within 500 flight cycles after June 11, 1993 (the effective date of AD 93-08-15, Amendment 39-8563 (58 FR 27923, May 12, 1993)), whichever occurs later, modify the inner rear spar web of the wing in accordance with Airbus Service Bulletin A320-57-1004, Revision 1, dated September 24, 1992; or Revision 2, dated June 14, 1993. As of the effective date of this AD, only Airbus Service Bulletin A320-57- 1004, Revision 2, dated June 14, 1993, may be used for the actions required by this paragraph. (h) Retained Cold Expansion of Holes at Forward Pintle Fitting and Actuating Cylinder Anchorage of the Main Landing Gear, With Change to Acceptable Service Information This paragraph restates the requirements of paragraph (b) of AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), with a change to acceptable service information. For airplanes having MSNs 002 through 051 inclusive, except airplanes modified as specified in Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001: Prior to the accumulation of 12,000 total flight cycles, or within 2,000 flight cycles after February 14, 1994 (the effective date of AD 93-25-13, Amendment 39-8777 (59 FR 1903, January 13, 1994)), whichever occurs later, accomplish the requirements of paragraphs (h)(1) and (h)(2) of this AD in accordance with Airbus Service Bulletin A320-57-1060, dated December 8, 1992; Revision 1, dated April 26, 1993; or Revision 2, dated December 16, 1994. As of the effective date of this AD, only Airbus Service Bulletin A320-57-1060, Revision 2, dated December 16, 1994, may be used for the actions required by this paragraph. (1) Perform a cold expansion of all the attachment holes for the forward pintle fitting of the main landing gear (MLG), except for the holes that are for taper-lok bolts. (2) Perform a cold expansion of the holes at the actuating cylinder anchorage of the MLG. (i) Retained Repetitive Ultrasonic Inspections for Cracking of the Rear Spar of the Wing, With No Changes This paragraph restates the requirements of paragraphs (c), (d), and (e) of AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), with no changes. Except for airplanes modified as specified in Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 03, dated February 9, 2001: Do the actions specified in paragraphs (i)(1) and (i)(2) of this AD. (1) Do an ultrasonic inspection for cracking of the rear spar of the wing, in accordance with Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001. Inspect at the applicable time specified in paragraph 1.E. of Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001, except as required by paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) For any airplane that has not been inspected but has exceeded the applicable specified compliance time in paragraph 1.E. of Airbus Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001, as of November 5, 2004 (the effective date of AD 2004-19-11, Amendment 39- 13805 (69 FR 58828, October 1, 2004)): Inspect within 18 months after November 5, 2004. (ii) For any airplane that has been inspected before November 5, 2004 (the effective date of AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004): Repeat the inspection within 3,600 flight cycles after the most recent inspection. (2) Repeat the inspection required by paragraph (i)(1) of this AD at intervals not to exceed 3,600 flight cycles or 6,700 flight hours, whichever occurs first, until the requirements of paragraph (k) of this AD have been done. (j) Retained Corrective Action for Inspections Required by Paragraphs (i)(1) and (i)(2) of This AD, With Specific Delegation Approval Language. This paragraph restates the requirements of paragraph (f) of AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), with specific delegation approval language. If any crack is found during any inspection required by paragraph (i)(1) or (i)(2) of this AD: Before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated agent); or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Accomplishment of a repair as required by this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (i)(2) of this AD. (k) New Requirement of This AD: Modification of Inner Rear Spar Before exceeding 48,000 flight cycles or 96,000 flight hours, whichever occurs first since first flight of the airplane: modify all specified fastener holes in the inner rear spar of the wing, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001; except where Airbus Service Bulletin A320-57-1089, Revision 03, dated February 9, 2001, specifies to contact Airbus for certain conditions, before further flight, repair using a method approved by the [[Page 74061]] Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Modification of all specified fastener holes in the rear spar of the wing terminates the initial and repetitive inspections required by paragraphs (i)(1) and (i)(2) of this AD. If the modification is done both before the airplane accumulates 12,000 total flight cycles and before the effective date of this AD, the modification also terminates the actions required by paragraphs (g) and (h) of this AD. (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-57-1088, Revision 02, dated July 29, 1999; or Revision 03, dated February 9, 2001, which are not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-57-1089, Revision 02, dated November 6, 1998, which is not incorporated by reference in this AD. (m) 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]. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously in accordance with AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), are approved as AMOCs for the corresponding provisions of paragraphs (g) through (j) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0169, corrected July 22, 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-2015-5811. (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 November 17, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-30006 Filed 11-25-15; 8:45 am] BILLING CODE 4910-13-P
![74058 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
searching for and locating Docket No. FAA– DATES: We must receive comments on 2014–NM–158–AD’’ at the beginning of
2015–5813. this proposed AD by January 11, 2016. your comments. We specifically invite
(2) For service information identified in comments on the overall regulatory,
ADDRESSES: You may send comments by
this AD, contact Dassault Falcon Jet, P.O. Box economic, environmental, and energy
2000, South Hackensack, NJ 07606; any of the following methods:
telephone 201–440–6700; Internet http:// • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
www.dassaultfalcon.com. You may view this http://www.regulations.gov. Follow the consider all comments received by the
service information at the FAA, Transport instructions for submitting comments. closing date and may amend this
Airplane Directorate, 1601 Lind Avenue SW., • Fax: 202–493–2251. proposed AD based on those comments.
Renton, WA. For information on the • Mail: U.S. Department of We will post all comments we
availability of this material at the FAA, call Transportation, Docket Operations, M– receive, without change, to http://
425–227–1221. 30, West Building Ground Floor, Room www.regulations.gov, including any
Issued in Renton, Washington, on W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
November 17, 2015. Washington, DC 20590. will also post a report summarizing each
Jeffrey E. Duven, • Hand Delivery: U.S. Department of substantive verbal contact we receive
Manager, Transport Airplane Directorate, Transportation, Docket Operations, M– about this proposed AD.
Aircraft Certification Service. 30, West Building Ground Floor, Room Discussion
[FR Doc. 2015–30022 Filed 11–25–15; 8:45 am] W12–140, 1200 New Jersey Avenue SE.,
BILLING CODE 4910–13–P Washington, DC, between 9 a.m. and 5 On September 21, 2004, we issued AD
p.m., Monday through Friday, except 2004–19–11, Amendment 39–13805 (69
Federal holidays. FR 58828, October 1, 2004). AD 2004–
DEPARTMENT OF TRANSPORTATION For service information identified in 19–11 requires actions intended to
this proposed AD, contact Airbus, address an unsafe condition on certain
Federal Aviation Administration Airworthiness Office—EIAS, 1 Rond Airbus Model 320 series airplanes. AD
Point Maurice Bellonte, 31707 Blagnac 2004–19–11 superseded AD 2000–10–
14 CFR Part 39 Cedex, France; telephone +33 5 61 93 36 15, Amendment 39–17739 (65 FR
96; fax +33 5 61 93 44 51; email 34069, May 26, 2000).
[Docket No. FAA–2015–5811; Directorate
Identifier 2014–NM–158–AD] account.airworth-eas@airbus.com; Since we issued AD 2004–19–11,
Internet http://www.airbus.com. You Amendment 39–13805 (69 FR 58828,
RIN 2120–AA64 may view this referenced service October 1, 2004), we have determined
information at the FAA, Transport that the modification of the inner rear
Airworthiness Directives; Airbus Airplane Directorate, 1601 Lind Avenue spar that is an optional terminating
Airplanes SW., Renton, WA. For information on action of AD 2004–19–11 must be
AGENCY: Federal Aviation the availability of this material at the accomplished in order to address the
Administration (FAA), DOT. FAA, call 425–227–1221. identified unsafe condition.
As described in FAA Advisory
ACTION: Notice of proposed rulemaking Examining the AD Docket Circular 120–104 (http://www.faa.gov/
(NPRM).
You may examine the AD docket on documentLibrary/media/Advisory_
SUMMARY: We propose to supersede the Internet at http:// Circular/120–104.pdf), several programs
Airworthiness Directive (AD) 2004–19– www.regulations.gov by searching for have been developed to support
11 for certain Airbus Model 320 series and locating Docket No. FAA–2015– initiatives that will ensure the
airplanes. AD 2004–19–11 currently 5811; or in person at the Docket continued airworthiness of aging
requires modification of the inner rear Management Facility between 9 a.m. airplane structure. The last element of
spar web of the wing, cold expansion of and 5 p.m., Monday through Friday, those initiatives is the requirement to
the attachment holes of the forward except Federal holidays. The AD docket establish a limit of validity (LOV) of the
pintle fitting and the actuating cylinder contains this proposed AD, the engineering data that support the
anchorage of the main landing gear regulatory evaluation, any comments structural maintenance program under
(MLG), repetitive ultrasonic inspections received, and other information. The 14 CFR 26.21. This proposed AD is the
for cracking of the rear spar of the wing, street address for the Docket Operations result of an assessment of the previously
and corrective action if necessary. AD office (telephone 800–647–5527) is in established programs by the design
2004–19–11 also provides optional the ADDRESSESsection. Comments will approval holder (DAH). The actions
terminating action for the repetitive be available in the AD docket shortly specified in this proposed AD are
inspections. Since we issued AD 2004– after receipt. necessary to complete certain programs
19–11, we have determined that the FOR FURTHER INFORMATION CONTACT: to ensure the continued airworthiness of
terminating action is necessary to Sanjay Ralhan, Aerospace Engineer, aging airplane structure and to support
address the unsafe condition. This International Branch, ANM–116, an airplane reaching its LOV.
proposed AD is intended to complete Transport Airplane Directorate, FAA, The European Aviation Safety
certain mandated programs intended to 1601 Lind Avenue SW., Renton, WA Agency, which is the Technical Agent
support the airplane reaching its limit of 98057–3356; telephone 425–227–1405; for the Member States of the European
validity (LOV) of the engineering data fax 425–227–1149. Union, has issued EASA Airworthiness
that support the established structural Directive 2014–0169, corrected July 22,
mstockstill on DSK4VPTVN1PROD with PROPOSALS
SUPPLEMENTARY INFORMATION:
maintenance program. This proposed 2014 (referred to after this as the
AD would retain the requirements of AD Comments Invited Mandatory Continuing Airworthiness
2004–19–11 and would require the We invite you to send any written Information, or ‘‘the MCAI’’), to correct
previously optional terminating action. relevant data, views, or arguments about an unsafe condition on certain Airbus
We are proposing this AD to prevent this proposed AD. Send your comments Model A320 series airplanes. The MCAI
fatigue cracking of the inner rear spar, to an address listed under the states:
which may lead to reduced structural ADDRESSES section. Include ‘‘Docket No. During centre fuselage certification full
integrity of the wing and the MLG. FAA–2015–5811; Directorate Identifier scale fatigue test, cracks were found on the
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inner rear spar at holes position 52 on the holes in the inner rear spar for the Part A, Subpart III, Section 44701:
right hand wing due to fatigue aspects. attachment of gear rib 5, forward pintle General requirements.’’ Under that
This condition, if not detected and fitting, and actuating cylinder section, Congress charges the FAA with
corrected, could affect the structural integrity promoting safe flight of civil aircraft in
anchorage; and the installation of
of the aeroplane.
To prevent such cracks, Airbus developed interference fit fasteners in the rear spar air commerce by prescribing regulations
modifications, which were introduced in and gear rib 5. for practices, methods, and procedures
production and in service through several This service information is reasonably the Administrator finds necessary for
Airbus Service Bulletins (SB). DGAC France available because the interested parties safety in air commerce. This regulation
issued * * * [an earlier AD], which was have access to it through their normal is within the scope of that authority
subsequently superseded by [DGAC] AD course of business or by the means because it addresses an unsafe condition
2001–249 [which corresponds with FAA AD identified in the ADDRESSESsection of that is likely to exist or develop on
2004–19–11, Amendment 39–13805 (69 FR this NPRM. products identified in this rulemaking
58828, October 1, 2004)], to require
action.
modification of the rear spar on some FAA’s Determination and Requirements
aeroplanes, post-modification repetitive of This Proposed AD Regulatory Findings
inspections and, depending on findings,
accomplishment of a repair. DGAC France This product has been approved by We determined that this proposed AD
AD 2001–249 also specified that modification the aviation authority of another would not have federalism implications
in accordance with Airbus SB A320–57–1089 country, and is approved for operation under Executive Order 13132. This
(in-service equivalent to Airbus mod 24591) in the United States. Pursuant to our proposed AD would not have a
constituted (optional) terminating action for bilateral agreement with the State of substantial direct effect on the States, on
the repetitive inspections. Design Authority, we have been notified the relationship between the national
Since that [DGAC] AD [2001–249] was of the unsafe condition described in the Government and the States, or on the
issued, in the framework of the A320 distribution of power and
Extended Service Goal (ESG), it has been
MCAI and service information
referenced above. We are proposing this responsibilities among the various
determined that Airbus mod 24591 is
necessary to allow aeroplanes to operate up AD because we evaluated all pertinent levels of government.
to the new ESG limit. information and determined an unsafe For the reasons discussed above, I
For the reasons described above, this condition exists and is likely to exist or certify this proposed regulation:
[EASA] AD retains the requirements of DGAC develop on other products of the same 1. Is not a ‘‘significant regulatory
France AD 2001–249, which is superseded, type design. action’’ under Executive Order 12866;
and requires modification of all pre-mod 2. Is not a ‘‘significant rule’’ under the
24591 aeroplanes. Costs of Compliance DOT Regulatory Policies and Procedures
The modification includes modifying We estimate that this proposed AD (44 FR 11034, February 26, 1979);
affects 84 airplanes of U.S. registry. 3. Will not affect intrastate aviation in
all specified fastener holes in the inner
The actions required by AD 2004–19– Alaska; and
rear spar of the wing. You may examine
11, Amendment 39–13805 (69 FR 4. Will not have a significant
the MCAI in the AD docket on the
58828, October 1, 2004), and retained in economic impact, positive or negative,
Internet at http://www.regulations.gov
this proposed AD take about 684 work- on a substantial number of small entities
by searching for and locating Docket No.
hours per product, at an average labor under the criteria of the Regulatory
FAA–2015–5811.
rate of $85 per work-hour. Required Flexibility Act.
Related Service Information Under 1 parts cost about $13,644 per product. List of Subjects in 14 CFR Part 39
CFR part 51 Based on these figures, the estimated Air transportation, Aircraft, Aviation
Airbus has issued the following cost of the actions that are required by safety, Incorporation by reference,
service information. AD 2004–19–11 is $71,784 per product. Safety.
• Airbus Service Bulletin A320–57– We also estimate that it would take
1004, Revision 02, dated June 14, 1993. about 980 work-hours per product to The Proposed Amendment
This service information describes comply with the basic requirements of Accordingly, under the authority
procedures for modifying the inner rear this proposed AD. The average labor delegated to me by the Administrator,
spar web of the wing. rate is $85 per work-hour. Required the FAA proposes to amend 14 CFR part
• Airbus Service Bulletin A320–57– parts would cost about $32,727 per 39 as follows:
1060, Revision 2, dated December 16, product. Based on these figures, we
1994. This service information describes estimate the cost of this proposed AD on PART 39—AIRWORTHINESS
procedures for a cold expansion of all U.S. operators to be $9,746,268, or DIRECTIVES
the attachment holes for the forward $116,027 per product.
pintle fitting of the main landing gear We have received no definitive data ■ 1. The authority citation for part 39
(MLG), except for the holes that are for that would enable us to provide cost continues to read as follows:
taper-lok bolts; and for a cold expansion estimates for the on-condition actions Authority: 49 U.S.C. 106(g), 40113, 44701.
of the holes at the actuating cylinder specified in this proposed AD.
anchorage of the MLG. § 39.13 [Amended]
• Airbus Mandatory Service Bulletin Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by
A320–57–1088, Revision 04, dated Title 49 of the United States Code removing Airworthiness Directive (AD)
August 6, 2001. This service specifies the FAA’s authority to issue 2004–19–11, Amendment 39–13805 (69
mstockstill on DSK4VPTVN1PROD with PROPOSALS
information describes procedures for rules on aviation safety. Subtitle I, FR 58828, October 1, 2004), and adding
doing ultrasonic inspections for section 106, describes the authority of the following new AD:
cracking of the rear spar of the wing. the FAA Administrator. ‘‘Subtitle VII: Airbus: Docket No. FAA–2015–5811;
• Airbus Service Bulletin A320–57– Aviation Programs,’’ describes in more Directorate Identifier 2014–NM–158–AD.
1089, Revision 03, dated February 9, detail the scope of the Agency’s
2001. This service information describes authority. (a) Comments Due Date
modification of the airplane by We are issuing this rulemaking under We must receive comments by
accomplishing cold reexpansion of the the authority described in ‘‘Subtitle VII, January 11, 2016.
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![Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74061
Manager, International Branch, ANM– accomplished using a method approved by DATES: Comments must be received on
116, Transport Airplane Directorate, the Manager, International Branch, ANM– or before January 26, 2016.
FAA; or EASA; or Airbus’s EASA DOA. 116, Transport Airplane Directorate, FAA; or
ADDRESSES: Send comments on this
the European Aviation Safety Agency
Modification of all specified fastener (EASA); or Airbus’ EASA Design proposal to the U.S. Department of
holes in the rear spar of the wing Organization Approval (DOA). If approved by Transportation, Docket Operations, M–
terminates the initial and repetitive the DOA, the approval must include the 30, 1200 New Jersey Avenue SE., West
inspections required by paragraphs (i)(1) DOA-authorized signature. Building Ground Floor, Room W12–140,
and (i)(2) of this AD. If the modification (n) Related Information Washington, DC 20590–0001; telephone:
is done both before the airplane (202) 366–9826. You must identify FAA
accumulates 12,000 total flight cycles (1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA Docket No. FAA–2015–4452 and
and before the effective date of this AD, Airworthiness Directive 2014–0169, Airspace Docket No. 15–AWA–7 at the
the modification also terminates the corrected July 22, 2014, for related beginning of your comments. You may
actions required by paragraphs (g) and information. This MCAI may be found in the also submit comments through the
(h) of this AD. AD docket on the Internet at http:// Internet at http://www.regulations.gov.
www.regulations.gov by searching for and You may review the public docket
(l) Credit for Previous Actions locating Docket No. FAA–2015–5811. containing the proposal, any comments
(1) This paragraph provides credit for (2) For service information identified in
this AD, contact Airbus, Airworthiness received, and any final disposition in
actions required by paragraph (i) of this person in the Dockets Office between
Office—EIAS, 1 Rond Point Maurice
AD, if those actions were performed Bellonte, 31707 Blagnac Cedex, France; 9:00 a.m. and 5:00 p.m., Monday
before the effective date of this AD using telephone +33 5 61 93 36 96; fax +33 5 61 through Friday, except Federal holidays.
Airbus Service Bulletin A320–57–1088, 93 44 51; email account.airworth-eas@ The Docket Office (telephone 1–800–
Revision 02, dated July 29, 1999; or airbus.com; Internet http://www.airbus.com. 647–5527), is on the ground floor of the
Revision 03, dated February 9, 2001, You may view this service information at the building at the above address.
which are not incorporated by reference FAA, Transport Airplane Directorate, 1601 FAA Order 7400.9Z, Airspace
in this AD. Lind Avenue SW., Renton, WA. For
information on the availability of this Designations and Reporting Points, and
(2) This paragraph provides credit for material at the FAA, call 425–227–1221. subsequent amendments can be viewed
actions required by paragraph (k) of this online at http://www.faa.gov/air_traffic/
AD, if those actions were performed Issued in Renton, Washington, on
November 17, 2015.
publications/. For further information,
before the effective date of this AD using you can contact the Airspace Policy
Airbus Service Bulletin A320–57–1089, Jeffrey E. Duven,
Group, Federal Aviation
Revision 02, dated November 6, 1998, Manager, Transport Airplane Directorate,
Administration, 800 Independence
which is not incorporated by reference Aircraft Certification Service.
Avenue SW., Washington, DC, 20591;
in this AD. [FR Doc. 2015–30006 Filed 11–25–15; 8:45 am]
telephone: (202) 267–8783. The Order is
BILLING CODE 4910–13–P
(m) Other FAA AD Provisions also available for inspection at the
National Archives and Records
The following provisions also apply to this Administration (NARA). For
AD: DEPARTMENT OF TRANSPORTATION
information on the availability of this
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International Federal Aviation Administration material at NARA, call (202) 741–6030,
Branch, ANM–116, Transport Airplane or go to http://www.archives.gov/
Directorate, FAA, has the authority to 14 CFR Part 71 federal_register/code_of_federal-
approve AMOCs for this AD, if requested regulations/ibr_locations.html.
using the procedures found in 14 CFR 39.19. [Docket No. FAA–2015–4452; Airspace FAA Order 7400.9, Airspace
In accordance with 14 CFR 39.19, send your Docket No. 15–AWA–7] Designations and Reporting Points, is
request to your principal inspector or local RIN 2120–AA66 published yearly and effective on
Flight Standards District Office, as September 15.
appropriate. If sending information directly Proposed Amendment of Class C FOR FURTHER INFORMATION CONTACT:
to the International Branch, send it to ATTN: Airspace; Capital Region International
Sanjay Ralhan, Aerospace Engineer, Colby Abbott, Airspace Policy Group,
Airport, MI Office of Airspace Services, Federal
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind AGENCY: Federal Aviation Aviation Administration, 800
Avenue SW., Renton, WA 98057–3356; Administration (FAA), DOT. Independence Avenue SW.,
telephone 425–227–1405; fax 425–227–1149. Washington, DC 20591; telephone: (202)
ACTION: Notice of proposed rulemaking
Information may be emailed to: 9-ANM-116- 267–8783.
AMOC-REQUESTS@faa.gov. (NPRM).
SUPPLEMENTARY INFORMATION:
(i) Before using any approved AMOC,
SUMMARY: This action proposes to
notify your appropriate principal inspector, Authority for This Rulemaking
or lacking a principal inspector, the manager
modify Class C airspace at Capital
of the local flight standards district office/ Region International Airport, formerly The FAA’s authority to issue rules
certificate holding district office. The AMOC Lansing Capital City Airport, Lansing, regarding aviation safety is found in
approval letter must specifically reference MI, by removing a cutout from the Title 49 of the United States Code.
this AD. surface area that was put in place to Subtitle I, Section 106 describes the
(ii) AMOCs approved previously in accommodate operations around Davis authority of the FAA Administrator.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
accordance with AD 2004–19–11, Airport, now permanently closed. Also, Subtitle VII, Aviation Programs,
Amendment 39–13805 (69 FR 58828, October this proposal would update the airport’s describes in more detail the scope of the
1, 2004), are approved as AMOCs for the name and geographic coordinates to agency’s authority. This rulemaking is
corresponding provisions of paragraphs (g)
through (j) of this AD.
reflect the current information in the promulgated under the authority
(2) Contacting the Manufacturer: As of the FAA’s aeronautical database. The FAA described in Subtitle VII, Part A,
effective date of this AD, for any requirement is proposing this action to enable more Subpart I, Section 40103. Under that
in this AD to obtain corrective actions from efficient operations at Capital Region section, the FAA is charged with
a manufacturer, the action must be International Airport. prescribing regulations to assign the use
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Document Created: 2015-12-14 14:05:38
Document Modified: 2015-12-14 14:05:38
| 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 January 11, 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 | 80 FR 74058 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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