81 FR 40210 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 119 (June 21, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 119 (June 21, 2016)
| Page Range | 40210-40213 | |
| FR Document | 2016-14301 |
[Federal Register Volume 81, Number 119 (Tuesday, June 21, 2016)] [Proposed Rules] [Pages 40210-40213] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-14301] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7262; Directorate Identifier 2015-NM-079-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) 98-13-14, for certain Airbus Model A320-211, -212, and -231 airplanes. AD 98-13- 14 currently requires repetitive rotating probe inspections of fastener holes and/or the adjacent tooling hole of a former junction of the aft fuselage, as applicable, and corrective action, if necessary. AD 98-13- 14 also provides for an optional terminating action for the repetitive inspections. Since we issued AD 98-13-14, an evaluation by the design approval holder (DAH) indicates that the former junction of the aft fuselage is subject to fatigue damage. This proposed AD would continue to require the actions in AD 98-13-14, with revised inspection compliance times. We are proposing this AD to detect and correct fatigue cracks in the former junction of the aft fuselage; fatigue cracking could propagate and could adversely affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by August 5, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M- [[Page 40211]] 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 NPRM, 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-2016- 7262; 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 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-2016-7262; Directorate Identifier 2015-NM-079-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 June 11, 1998, we issued AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998) (``AD 98-13-14''). AD 98-13-14 requires actions intended to address an unsafe condition on certain Airbus Model A320 series airplanes. AD 98-13-14 was prompted by a report that four cracks were identified in the fastener holes of the former junction at frame (FR) 68 between stringers 4 and 5, which occurred during a full scale fatigue test. AD 98-13-14 requires repetitive rotating probe inspections of fastener holes and/or the adjacent tooling hole of a former junction of the aft fuselage, and corrective action, if necessary. AD 98-13-14 also provides for an optional terminating action for the repetitive inspections. We issued AD 98-13-14 to prevent reduced structural integrity of the aft fuselage caused by fatigue cracking of the former junction at FR 68. Since we issued AD 98-13-14, an evaluation by the DAH indicates that the former junction of the aft fuselage is subject to fatigue damage. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015-0084, dated May 13, 2015; corrected May 18, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A320-211, -212, and -231 airplanes. The MCAI states: During a fatigue test campaign, four cracks were identified in the fastener holes of the former junction at frame (FR) 68 between stringers 4 and 5. This condition, if not detected and corrected, could lead to crack propagation, possibly resulting in reduced structural integrity of the fuselage. To address this unsafe condition, DGAC [Direction g[eacute]n[eacute]rale de l'aviation civile] France issued * * * [an AD, which corresponds to FAA AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998)] to require repetitive inspections and, depending on findings, the accomplishment of an applicable repair solution. That [DGAC] AD also provided modification of FR 68 [cold working of fastener and tooling holes] in accordance with Airbus Service Bulletin (SB) A320-53-1090 as optional terminating action. Following new analyses, the thresholds and inspection intervals have been reviewed and adjusted. For the reason described above, this [EASA] AD retains the requirements of DGAC France AD 96-298-093(B)R2 [http://ad.easa.europa.eu/ad/F-1996-298R2], which is superseded, and requires those actions within the new thresholds and intervals. This [EASA] AD was republished to correct a typographical error in the Reason. Repairs include doing applicable related investigative actions (i.e., rotating probe inspection of the hole to make sure the crack is removed and eddy current inspection of the cold expanded holes). 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-2016- 7262. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: Service Bulletin A320-53-1089, Revision 03, dated March 18, 2015. This service information describes procedures for a rotating probe inspection for fatigue cracking of the frame junction holes and the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, and repair, including doing applicable related investigative actions. Service Bulletin A320-53-1090, Revision 02, dated December 22, 1998. This service information describes procedures for modifying the airplane (cold working of fastener and tooling holes). This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination 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 10 airplanes of U.S. registry. The actions required by AD 98-13-14 and retained in this proposed AD take about 8 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 98-13-14 is $680 per product, per inspection cycle. We also estimate that it would take about 4 work-hours per product to [[Page 40212]] comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $3,400, or $340 per product. In addition, we estimate that any necessary follow-on repairs would take about 52 work-hours and require parts costing $3,800, for a cost of $8,220 per product. We have no way of determining the number of aircraft that might need these actions. 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) 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998), and adding the following new AD: Airbus: Docket No. FAA-2016-7262; Directorate Identifier 2015-NM- 079-AD. (a) Comments Due Date We must receive comments by August 5, 2016. (b) Affected ADs This AD replaces AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998) (``AD 98-13-14''). (c) Applicability This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers (S/Ns) 0001 through 0123 inclusive, except those that have embodied Airbus Modifications 21780 and 21781 in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by identification of four cracks in the fastener holes of the former junction at frame (FR) 68 between stringers 4 and 5, which occurred during a fatigue test campaign, and a determination that certain compliance times specified in AD 98-13-14 must be reduced. We are issuing this AD to prevent fatigue cracks from occurring or propagating in certain structure which could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections and Repair With Revised Compliance Language, and Additional Methods of Approving Repairs This paragraph restates the requirements of paragraph (a) of AD 98-13-14, with revised compliance language; and adds additional methods of approving repairs. For Model A320 series airplanes, as listed in Airbus Service Bulletins A320-53-1089 and A320-53-1090, both dated November 22, 1995: Prior to the accumulation of 20,000 total flight cycles, or within 500 flight cycles after July 30, 1998 (the effective date of AD 98-13-14), whichever occurs later, perform a rotating probe inspection for fatigue cracking of the fastener holes and/or the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, dated November 22, 1995. Accomplishing an inspection required by paragraph (h) of this AD terminates the actions required by this paragraph. (1) If no crack is detected, accomplish either paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Repeat the inspection thereafter at intervals not to exceed 20,000 flight cycles; or (ii) Prior to further flight following the accomplishment of the inspection required by paragraph (g) of this AD, cold work the fastener holes and/or the adjacent tooling hole of the right- and left-hand former junctions at FR 68, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1090, dated November 22, 1995. Accomplishment of this cold working constitutes terminating action for the repetitive inspections required by paragraph (g)(1)(i) of this AD. (2) If any crack is detected, prior to further flight, repair it in accordance with 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). (h) New Repetitive Inspection Requirement Within the compliance time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, whichever occurs latest: Accomplish a rotating probe inspection for fatigue cracking of the frame junction holes and the adjacent tooling hole, as applicable, of the right- and left-hand former junctions at FR 68, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 03, dated March 18, 2015. Repeat the inspection thereafter at intervals not to exceed 3,800 flight cycles or 7,600 flight hours, whichever occurs first, until a repair required by paragraph (i) of this AD is done or a modification specified in paragraph (j) of this AD is done. Accomplishing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD. (1) Within 28,700 flight cycles or 57,400 flight hours since airplane first flight, whichever occurs first; or (2) Within 3,800 flight cycles or 7,600 flight hours, whichever occurs first, since the most recent inspection done in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 03, dated March 18, 2015; or (3) Within 3,800 flight cycles or 7,600 flight hours after the effective date of this AD, whichever occurs first, without exceeding 20,000 flight cycles since the most recent inspection done in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 03, dated March 18, 2015. [[Page 40213]] (i) New Repair Requirement If any crack is detected during any inspection required by paragraph (h) of this AD: Before further flight, repair, including doing all applicable related investigative actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 03, dated March 18, 2015. Do all applicable related investigative actions before further flight. Repair of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1089, Revision 03, dated March 18, 2015, constitutes terminating action for the repetitive inspections required by paragraph (h) of this AD. (j) New Optional Modification Modification of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1090, Revision 02, dated December 22, 1998, constitutes terminating action for the repetitive inspections required by paragraph (h) of this AD, provided the modification is accomplished before further flight after accomplishing an inspection required by paragraph (h) of this AD and no cracks were detected. (k) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD, which are not incorporated by reference in this AD. (i) Airbus Service Bulletin A320-53-1089, Revision 01, dated June 4, 1998; (ii) Airbus Service Bulletin A320-53-1089, Revision 02, dated February 3, 2003. (2) This paragraph provides credit for the actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD in accordance with the service information identified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. (i) Airbus Service Bulletin A320-53-1090, dated November 22, 1995, which was incorporated by reference in AD 98-13-14, Amendment 39-10602 (63 FR 34556, June 25, 1998). (ii) Airbus Service Bulletin A320-53-1090, Revision 1, dated November 22, 1995, dated June 10, 1998, which is not incorporated by reference in this AD. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: 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. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0084, dated May 13, 2015; corrected May 18, 2015, 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-2016-7262. (2) For service information identified in this AD, contact Airbus SAS, 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 June 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-14301 Filed 6-20-16; 8:45 am] BILLING CODE 4910-13-P
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The Boeing Company: Docket No. FAA– (ii) On areas that are not repaired, repeat Issued in Renton, Washington, on June 3,
2016–6901; Directorate Identifier 2015– the inspections thereafter at the applicable 2016.
NM–192–AD. times specified in paragraph 1.E., Michael Kaszycki,
‘‘Compliance,’’ of Boeing Alert Service
(a) Comments Due Date Acting Manager, Transport Airplane
Bulletin 737–53A1248, Revision 2, dated
We must receive comments by August 5, Directorate, Aircraft Certification Service.
October 14, 2015.
2016. [FR Doc. 2016–14295 Filed 6–20–16; 8:45 am]
(h) Terminating Action for AD 2005–21–06 BILLING CODE 4910–13–P
(b) Affected ADs
Accomplishment of the initial inspections
Certain requirements of this AD terminate required by paragraph (g) of this AD
certain requirements of AD 2005–21–06, terminates the requirements of AD 2005–21– DEPARTMENT OF TRANSPORTATION
Amendment 39–14344 (70 FR 61226, October 06.
21, 2005) (‘‘AD 2005–21–06’’).
(i) Credit for Previous Actions Federal Aviation Administration
(c) Applicability
This paragraph provides credit for the
This AD applies to The Boeing Company actions specified in paragraph (g) of this AD, 14 CFR Part 39
Model 737–600, –700, –700C, –800, and –900 if those actions were performed before the [Docket No. FAA–2016–7262; Directorate
series airplanes, certificated in any category, effective date of this AD using Boeing Alert Identifier 2015–NM–079–AD]
line number 1 through 1755, as identified in Service Bulletin 737–53A1248, dated
Boeing Alert Service Bulletin 737–53A1248, September 9, 2004; or Boeing Alert Service RIN 2120–AA64
Revision 2, dated October 14, 2015. Bulletin 737–53A1248, Revision 1, dated
(d) Subject September 10, 2007; which are not Airworthiness Directives; Airbus
incorporated by reference in this AD. Airplanes
Air Transport Association (ATA) of
America Code 53, Fuselage. (j) Alternative Methods of Compliance AGENCY: Federal Aviation
(AMOCs) Administration (FAA), DOT.
(e) Unsafe Condition
(1) The Manager, Seattle Aircraft ACTION: Notice of proposed rulemaking
This AD was prompted by an evaluation by Certification Office (ACO), FAA, has the
the design approval holder (DAH) indicating (NPRM).
authority to approve AMOCs for this AD, if
that the aft pressure bulkhead is subject to
requested using the procedures found in 14 SUMMARY: We propose to supersede
widespread fatigue damage (WFD). We are
CFR 39.19. In accordance with 14 CFR 39.19,
issuing this AD to detect and correct cracks
send your request to your principal inspector
Airworthiness Directive (AD) 98–13–14,
in the aft pressure bulkhead web, which for certain Airbus Model A320–211,
or local Flight Standards District Office, as
could result in an uncontrolled –212, and –231 airplanes. AD 98–13–14
appropriate. If sending information directly
decompression of the fuselage. currently requires repetitive rotating
to the manager of the ACO, send it to the
(f) Compliance attention of the person identified in probe inspections of fastener holes and/
Comply with this AD within the paragraph (k)(1) of this AD. Information may or the adjacent tooling hole of a former
compliance times specified, unless already be emailed to: 9-ANM-Seattle-ACO-AMOC- junction of the aft fuselage, as
done. Requests@faa.gov. applicable, and corrective action, if
(2) Before using any approved AMOC,
(g) Repetitive Inspections notify your appropriate principal inspector,
necessary. AD 98–13–14 also provides
or lacking a principal inspector, the manager for an optional terminating action for
At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing of the local flight standards district office/ the repetitive inspections. Since we
Alert Service Bulletin 737–53A1248, certificate holding district office. issued AD 98–13–14, an evaluation by
Revision 2, dated October 14, 2015, or within (3) An AMOC that provides an acceptable the design approval holder (DAH)
18 months after November 25, 2005 (the level of safety may be used for any repair, indicates that the former junction of the
effective date of AD 2005–21–06), whichever modification, or alteration required by this aft fuselage is subject to fatigue damage.
occurs later: Do a low frequency eddy current AD if it is approved by the Boeing This proposed AD would continue to
(LFEC) or high frequency eddy current Commercial Airplanes Organization
Designation Authorization (ODA) that has
require the actions in AD 98–13–14,
(HFEC) inspection, and a detailed inspection,
of the aft and forward sides, as applicable, of been authorized by the Manager, Seattle with revised inspection compliance
the aft pressure bulkhead web at the Y chord, ACO, to make those findings. To be times. We are proposing this AD to
above and below stringer S–15L and stringer approved, the repair method, modification detect and correct fatigue cracks in the
S–15R, to detect discrepancies (including deviation, or alteration deviation must meet former junction of the aft fuselage;
cracking, crack indications, discrepant the certification basis of the airplane, and the fatigue cracking could propagate and
fastener holes, and corrosion), in accordance approval must specifically refer to this AD. could adversely affect the structural
with the Accomplishment Instructions of integrity of the airplane.
(k) Related Information
Boeing Alert Service Bulletin 737–53A1248,
Revision 2, dated October 14, 2015. Access (1) For more information about this AD, DATES: We must receive comments on
and restoration procedures specified in the contact Alan Pohl, Aerospace Engineer, this proposed AD by August 5, 2016.
Accomplishment Instructions of Boeing Alert Airframe Branch, ANM–120S, FAA, Seattle ADDRESSES: You may send comments,
Service Bulletin 737–53A1248, Revision 2, Aircraft Certification Office (ACO), 1601 Lind using the procedures found in 14 CFR
dated October 14, 2015, are not required by Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6450; fax: 425–917–6590; 11.43 and 11.45, by any of the following
this AD. Operators may do those procedures
following their maintenance practices. email: Alan.Pohl@faa.gov. methods:
(1) If no discrepancy is found: Repeat the (2) For service information identified in • Federal eRulemaking Portal: Go to
inspections thereafter at the applicable times this AD, contact Boeing Commercial http://www.regulations.gov. Follow the
specified in paragraph 1.E., ‘‘Compliance,’’ of Airplanes, Attention: Data & Services instructions for submitting comments.
rmajette on DSK2TPTVN1PROD with PROPOSALS
Boeing Alert Service Bulletin 737–53A1248, Management, P.O. Box 3707, MC 2H–65, • Fax: 202–493–2251.
Revision 2, dated October 14, 2015. Seattle, WA 98124–2207; telephone 206– • Mail: U.S. Department of
(2) If any discrepancy is found: Do the 544–5000, extension 1; fax 206–766–5680; Transportation, Docket Operations, M–
actions specified in paragraphs (g)(2)(i) and Internet https://www.myboeingfleet.com. You
(g)(2)(ii) of this AD. may view this referenced service information
30, West Building Ground Floor, Room
(i) Repair the discrepancy before further at the FAA, Transport Airplane Directorate, W12–140, 1200 New Jersey Avenue SE.,
flight using a method approved in 1601 Lind Avenue SW., Renton, WA. For Washington, DC 20590.
accordance with the procedures specified in information on the availability of this • Hand Delivery: U.S. Department of
paragraph (j) of this AD. material at the FAA, call 425–227–1221. Transportation, Docket Operations, M–
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30, West Building Ground Floor, Room Discussion This [EASA] AD was republished to correct
W12–140, 1200 New Jersey Avenue SE., a typographical error in the Reason.
Washington, DC, between 9 a.m. and 5 On June 11, 1998, we issued AD 98–
13–14, Amendment 39–10602 (63 FR Repairs include doing applicable
p.m., Monday through Friday, except related investigative actions (i.e.,
Federal holidays. 34556, June 25, 1998) (‘‘AD 98–13–14’’).
AD 98–13–14 requires actions intended rotating probe inspection of the hole to
For service information identified in make sure the crack is removed and
this NPRM, contact Airbus, to address an unsafe condition on
certain Airbus Model A320 series eddy current inspection of the cold
Airworthiness Office—EIAS, 1 Rond expanded holes). You may examine the
Point Maurice Bellonte, 31707 Blagnac airplanes. AD 98–13–14 was prompted
by a report that four cracks were MCAI in the AD docket on the Internet
Cedex, France; telephone +33 5 61 93 36 at http://www.regulations.gov by
96; fax +33 5 61 93 44 51; email identified in the fastener holes of the
former junction at frame (FR) 68 searching for and locating Docket No.
account.airworth-eas@airbus.com; FAA–2016–7262.
Internet http://www.airbus.com. You between stringers 4 and 5, which
may view this referenced service occurred during a full scale fatigue test. Related Service Information Under 1
information at the FAA, Transport AD 98–13–14 requires repetitive CFR Part 51
Airplane Directorate, 1601 Lind Avenue rotating probe inspections of fastener Airbus has issued the following
SW., Renton, WA. For information on holes and/or the adjacent tooling hole of service information:
the availability of this material at the a former junction of the aft fuselage, and • Service Bulletin A320–53–1089,
FAA, call 425 227–1221. corrective action, if necessary. AD 98– Revision 03, dated March 18, 2015. This
13–14 also provides for an optional service information describes
Examining the AD Docket terminating action for the repetitive procedures for a rotating probe
You may examine the AD docket on inspections. We issued AD 98–13–14 to inspection for fatigue cracking of the
the Internet at http:// prevent reduced structural integrity of frame junction holes and the adjacent
www.regulations.gov by searching for the aft fuselage caused by fatigue tooling hole, as applicable, of the right-
and locating Docket No. FAA–2016– cracking of the former junction at FR 68. and left-hand former junctions at FR 68,
7262; or in person at the Docket Since we issued AD 98–13–14, an and repair, including doing applicable
Management Facility between 9 a.m. evaluation by the DAH indicates that related investigative actions.
and 5 p.m., Monday through Friday, the former junction of the aft fuselage is • Service Bulletin A320–53–1090,
except Federal holidays. The AD docket subject to fatigue damage. Revision 02, dated December 22, 1998.
contains this proposed AD, the The European Aviation Safety Agency This service information describes
regulatory evaluation, any comments (EASA), which is the Technical Agent procedures for modifying the airplane
received, and other information. The for the Member States of the European (cold working of fastener and tooling
street address for the Docket Operations Union, has issued EASA AD 2015–0084, holes).
office (telephone 800–647–5527) is in dated May 13, 2015; corrected May 18, This service information is reasonably
the ADDRESSES section. Comments will 2015 (referred to after this as the available because the interested parties
be available in the AD docket shortly Mandatory Continuing Airworthiness have access to it through their normal
after receipt. Information, or ‘‘the MCAI’’), to correct course of business or by the means
FOR FURTHER INFORMATION CONTACT: an unsafe condition for certain Airbus identified in the ADDRESSES section.
Sanjay Ralhan, Aerospace Engineer, Model A320–211, –212, and –231 FAA’s Determination and Requirements
International Branch, ANM–116, airplanes. The MCAI states: of This Proposed AD
Transport Airplane Directorate, FAA, During a fatigue test campaign, four cracks This product has been approved by
1601 Lind Avenue SW., Renton, WA were identified in the fastener holes of the
the aviation authority of another
98057–3356; telephone 425–227–1405; former junction at frame (FR) 68 between
stringers 4 and 5. country, and is approved for operation
fax 425–227–1149. in the United States. Pursuant to our
This condition, if not detected and
SUPPLEMENTARY INFORMATION: bilateral agreement with the State of
corrected, could lead to crack propagation,
Comments Invited possibly resulting in reduced structural Design Authority, we have been notified
integrity of the fuselage. of the unsafe condition described in the
We invite you to send any written To address this unsafe condition, DGAC MCAI and service information
relevant data, views, or arguments about [Direction générale de l’aviation civile] referenced above. We are proposing this
this proposed AD. Send your comments France issued * * * [an AD, which AD because we evaluated all pertinent
to an address listed under the corresponds to FAA AD 98–13–14,
information and determined an unsafe
ADDRESSES section. Include ‘‘Docket No. Amendment 39–10602 (63 FR 34556, June
25, 1998)] to require repetitive inspections condition exists and is likely to exist or
FAA–2016–7262; Directorate Identifier develop on other products of the same
2015–NM–079–AD’’ at the beginning of and, depending on findings, the
accomplishment of an applicable repair type design.
your comments. We specifically invite solution.
comments on the overall regulatory, Costs of Compliance
That [DGAC] AD also provided
economic, environmental, and energy modification of FR 68 [cold working of We estimate that this proposed AD
aspects of this proposed AD. We will fastener and tooling holes] in accordance affects 10 airplanes of U.S. registry.
consider all comments received by the with Airbus Service Bulletin (SB) A320–53– The actions required by AD 98–13–14
closing date and may amend this 1090 as optional terminating action. and retained in this proposed AD take
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proposed AD based on those comments. Following new analyses, the thresholds about 8 work-hours per product, at an
We will post all comments we and inspection intervals have been reviewed average labor rate of $85 per work-hour.
receive, without change, to http:// and adjusted.
For the reason described above, this
Based on these figures, the estimated
www.regulations.gov, including any [EASA] AD retains the requirements of DGAC cost of the actions that are required by
personal information you provide. We France AD 96–298–093(B)R2 [http:// AD 98–13–14 is $680 per product, per
will also post a report summarizing each ad.easa.europa.eu/ad/F-1996-298R2], which inspection cycle.
substantive verbal contact we receive is superseded, and requires those actions We also estimate that it would take
about this proposed AD. within the new thresholds and intervals. about 4 work-hours per product to
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![40212 Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Proposed Rules
comply with the basic requirements of The Proposed Amendment flight cycles, or within 500 flight cycles after
this AD. The average labor rate is $85 July 30, 1998 (the effective date of AD 98–
Accordingly, under the authority 13–14), whichever occurs later, perform a
per work-hour. Based on these figures, delegated to me by the Administrator, rotating probe inspection for fatigue cracking
we estimate the cost of this AD on U.S. the FAA proposes to amend 14 CFR part of the fastener holes and/or the adjacent
operators to be $3,400, or $340 per 39 as follows: tooling hole, as applicable, of the right- and
product. left-hand former junctions at FR 68, in
In addition, we estimate that any PART 39—AIRWORTHINESS accordance with the Accomplishment
necessary follow-on repairs would take DIRECTIVES Instructions of Airbus Service Bulletin A320–
about 52 work-hours and require parts 53–1089, dated November 22, 1995.
costing $3,800, for a cost of $8,220 per ■ 1. The authority citation for part 39 Accomplishing an inspection required by
product. We have no way of continues to read as follows: paragraph (h) of this AD terminates the
actions required by this paragraph.
determining the number of aircraft that Authority: 49 U.S.C. 106(g), 40113, 44701. (1) If no crack is detected, accomplish
might need these actions. either paragraph (g)(1)(i) or (g)(1)(ii) of this
§ 39.13 [Amended] AD.
Authority for This Rulemaking
■ 2. The FAA amends § 39.13 by (i) Repeat the inspection thereafter at
Title 49 of the United States Code removing Airworthiness Directive (AD) intervals not to exceed 20,000 flight cycles;
specifies the FAA’s authority to issue 98–13–14, Amendment 39–10602 (63 or
rules on aviation safety. Subtitle I, FR 34556, June 25, 1998), and adding (ii) Prior to further flight following the
section 106, describes the authority of accomplishment of the inspection required
the following new AD: by paragraph (g) of this AD, cold work the
the FAA Administrator. ‘‘Subtitle VII:
Airbus: Docket No. FAA–2016–7262; fastener holes and/or the adjacent tooling
Aviation Programs,’’ describes in more Directorate Identifier 2015–NM–079–AD. hole of the right- and left-hand former
detail the scope of the Agency’s junctions at FR 68, as applicable, in
authority. (a) Comments Due Date accordance with the Accomplishment
We are issuing this rulemaking under We must receive comments by August 5, Instructions of Airbus Service Bulletin A320–
the authority described in ‘‘Subtitle VII, 2016. 53–1090, dated November 22, 1995.
Part A, Subpart III, Section 44701: Accomplishment of this cold working
(b) Affected ADs constitutes terminating action for the
General requirements.’’ Under that
This AD replaces AD 98–13–14, repetitive inspections required by paragraph
section, Congress charges the FAA with
Amendment 39–10602 (63 FR 34556, June (g)(1)(i) of this AD.
promoting safe flight of civil aircraft in 25, 1998) (‘‘AD 98–13–14’’). (2) If any crack is detected, prior to further
air commerce by prescribing regulations flight, repair it in accordance with a method
for practices, methods, and procedures (c) Applicability
approved by the Manager, International
the Administrator finds necessary for This AD applies to Airbus Model A320– Branch, ANM–116, Transport Airplane
safety in air commerce. This regulation 211, –212, and –231 airplanes, certificated in Directorate, FAA; or the European Aviation
is within the scope of that authority any category, manufacturer serial numbers Safety Agency (EASA); or Airbus’s EASA
because it addresses an unsafe condition (S/Ns) 0001 through 0123 inclusive, except Design Organization Approval (DOA).
those that have embodied Airbus
that is likely to exist or develop on (h) New Repetitive Inspection Requirement
Modifications 21780 and 21781 in
products identified in this rulemaking production. Within the compliance time specified in
action. paragraph (h)(1), (h)(2), or (h)(3) of this AD,
(d) Subject whichever occurs latest: Accomplish a
Regulatory Findings
Air Transport Association (ATA) of rotating probe inspection for fatigue cracking
We determined that this proposed AD America Code 53, Fuselage. of the frame junction holes and the adjacent
would not have federalism implications tooling hole, as applicable, of the right- and
(e) Reason left-hand former junctions at FR 68, in
under Executive Order 13132. This
proposed AD would not have a This AD was prompted by identification of accordance with the Accomplishment
four cracks in the fastener holes of the former Instructions of Airbus Service Bulletin A320–
substantial direct effect on the States, on junction at frame (FR) 68 between stringers 53–1089, Revision 03, dated March 18, 2015.
the relationship between the national 4 and 5, which occurred during a fatigue test Repeat the inspection thereafter at intervals
Government and the States, or on the campaign, and a determination that certain not to exceed 3,800 flight cycles or 7,600
distribution of power and compliance times specified in AD 98–13–14 flight hours, whichever occurs first, until a
responsibilities among the various must be reduced. We are issuing this AD to repair required by paragraph (i) of this AD is
levels of government. prevent fatigue cracks from occurring or done or a modification specified in paragraph
For the reasons discussed above, I propagating in certain structure which could (j) of this AD is done. Accomplishing an
certify this proposed regulation: adversely affect the structural integrity of the inspection required by this paragraph
1. Is not a ‘‘significant regulatory airplane. terminates the inspections required by
paragraph (g) of this AD.
action’’ under Executive Order 12866; (f) Compliance (1) Within 28,700 flight cycles or 57,400
2. Is not a ‘‘significant rule’’ under the Comply with this AD within the flight hours since airplane first flight,
DOT Regulatory Policies and Procedures compliance times specified, unless already whichever occurs first; or
(44 FR 11034, February 26, 1979); done. (2) Within 3,800 flight cycles or 7,600
3. Will not affect intrastate aviation in flight hours, whichever occurs first, since the
Alaska; and (g) Retained Repetitive Inspections and most recent inspection done in accordance
Repair With Revised Compliance Language,
4. Will not have a significant with the Accomplishment Instructions of
and Additional Methods of Approving Airbus Service Bulletin A320–53–1089,
economic impact, positive or negative, Repairs
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on a substantial number of small entities Revision 03, dated March 18, 2015; or
This paragraph restates the requirements of (3) Within 3,800 flight cycles or 7,600
under the criteria of the Regulatory
paragraph (a) of AD 98–13–14, with revised flight hours after the effective date of this AD,
Flexibility Act. compliance language; and adds additional whichever occurs first, without exceeding
List of Subjects in 14 CFR Part 39 methods of approving repairs. For Model 20,000 flight cycles since the most recent
A320 series airplanes, as listed in Airbus inspection done in accordance with the
Air transportation, Aircraft, Aviation Service Bulletins A320–53–1089 and A320– Accomplishment Instructions of Airbus
safety, Incorporation by reference, 53–1090, both dated November 22, 1995: Service Bulletin A320–53–1089, Revision 03,
Safety. Prior to the accumulation of 20,000 total dated March 18, 2015.
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![Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Proposed Rules 40213
(i) New Repair Requirement Avenue SW., Renton, WA 98057–3356; DEPARTMENT OF TRANSPORTATION
If any crack is detected during any telephone 425–227–1405; fax 425–227–1149.
inspection required by paragraph (h) of this Information may be emailed to: 9-ANM-116- Federal Aviation Administration
AD: Before further flight, repair, including AMOC-REQUESTS@faa.gov. Before using
doing all applicable related investigative any approved AMOC, notify your appropriate 14 CFR Part 71
actions, in accordance with the principal inspector, or lacking a principal
Accomplishment Instructions of Airbus [Docket No. FAA–2014–0726; Airspace
inspector, the manager of the local flight
Service Bulletin A320–53–1089, Revision 03, Docket No. 14–ASO–9]
standards district office/certificate holding
dated March 18, 2015. Do all applicable
district office. The AMOC approval letter Proposed Amendment of Class D and
related investigative actions before further
flight. Repair of an airplane in accordance must specifically reference this AD. E Airspace, and Revocation of Class E
with the Accomplishment Instructions of (2) Contacting the Manufacturer: For any Airspace; Troy, AL
Airbus Service Bulletin A320–53–1089, requirement in this AD to obtain corrective
Revision 03, dated March 18, 2015, actions from a manufacturer, the action must AGENCY: Federal Aviation
constitutes terminating action for the be accomplished using a method approved Administration (FAA), DOT.
repetitive inspections required by paragraph by the Manager, International Branch, ANM– ACTION: Notice of proposed rulemaking
(h) of this AD. 116, Transport Airplane Directorate, FAA; or (NPRM).
(j) New Optional Modification the EASA; or Airbus’s EASA DOA. If
Modification of an airplane, in accordance
approved by the DOA, the approval must SUMMARY: This action proposes to
with the Accomplishment Instructions of include the DOA-authorized signature. amend Class D and E airspace, and
Airbus Service Bulletin A320–53–1090, (3) Required for Compliance (RC): If any remove Class E airspace designated as
Revision 02, dated December 22, 1998, service information contains procedures or an extension at Troy Municipal Airport
constitutes terminating action for the tests that are identified as RC, those at N. Kenneth Campbell Field (formerly
repetitive inspections required by paragraph procedures and tests must be done to comply Troy Municipal Airport), Troy, AL. The
(h) of this AD, provided the modification is with this AD; any procedures or tests that are Troy VHF Omnidirectional Radio Range
accomplished before further flight after not identified as RC are recommended. Those (VOR) has been decommissioned,
accomplishing an inspection required by procedures and tests that are not identified therefore Class E extension airspace is
paragraph (h) of this AD and no cracks were as RC may be deviated from using accepted
detected. no longer needed, and new Standard
methods in accordance with the operator’s Instrument Approach Procedures have
(k) Credit for Previous Actions maintenance or inspection program without been developed for Class D airspace and
(1) This paragraph provides credit for obtaining approval of an AMOC, provided Class E airspace extending upward from
actions required by paragraphs (h) and (i) of the procedures and tests identified as RC can 700 feet above the surface at the airport.
this AD, if those actions were performed be done and the airplane can be put back in This action would enhance the safety
before the effective date of this AD using the an airworthy condition. Any substitutions or and airspace management of Instrument
service information identified in paragraphs changes to procedures or tests identified as Flight Rules (IFR) operations at the
(k)(1)(i) and (k)(1)(ii) of this AD, which are RC require approval of an AMOC.
not incorporated by reference in this AD. airport. This action also would update
(i) Airbus Service Bulletin A320–53–1089, (m) Related Information the geographic coordinates of the airport
Revision 01, dated June 4, 1998; (1) Refer to Mandatory Continuing and recognize the name change of the
(ii) Airbus Service Bulletin A320–53–1089, Airworthiness Information (MCAI) EASA AD airport.
Revision 02, dated February 3, 2003. 2015–0084, dated May 13, 2015; corrected DATES: Comments must be received on
(2) This paragraph provides credit for the
May 18, 2015, for related information. This or before August 5, 2016.
actions required by paragraph (j) of this AD,
if those actions were performed before the MCAI may be found in the AD docket on the ADDRESSES: Send comments on this
effective date of this AD in accordance with Internet at http://www.regulations.gov by proposal to: U.S. Department of
the service information identified in searching for and locating Docket No. FAA– Transportation, Docket Operations, 1200
paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. 2016–7262. New Jersey Avenue SE., West Bldg
(i) Airbus Service Bulletin A320–53–1090, (2) For service information identified in Ground Floor Rm W12–140,
dated November 22, 1995, which was this AD, contact Airbus SAS, Airworthiness
Washington, DC 20590–0001;
incorporated by reference in AD 98–13–14, Office– EIAS, 1 Rond Point Maurice Bellonte,
Amendment 39–10602 (63 FR 34556, June Telephone: 1–800–647–5527; Fax: 202–
31707 Blagnac Cedex, France; telephone +33
25, 1998). 493–2251. You must identify the Docket
5 61 93 36 96; fax +33 5 61 93 44 51; email
(ii) Airbus Service Bulletin A320–53–1090, Number FAA–2014–0726; Airspace
account.airworth-eas@airbus.com; Internet
Revision 1, dated November 22, 1995, dated Docket No. 14–ASO–9, at the beginning
http://www.airbus.com. You may view this
June 10, 1998, which is not incorporated by of your comments. You may also submit
service information at the FAA, Transport
reference in this AD. and review received comments through
Airplane Directorate, 1601 Lind Avenue SW.,
(l) Other FAA AD Provisions Renton, WA. For information on the
the Internet at http://
availability of this material at the FAA, call
www.regulations.gov. You may review
The following provisions also apply to this
AD: 425–227–1221. the public docket containing the
(1) Alternative Methods of Compliance proposal, any comments received, and
Issued in Renton, Washington, on June 3, any final disposition in person in the
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane 2016. Dockets Office between 9:00 a.m. and
Directorate, FAA, has the authority to Michael Kaszycki, 5:00 p.m., Monday through Friday,
approve AMOCs for this AD, if requested Acting Manager, Transport Airplane except Federal holidays. The Docket
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using the procedures found in 14 CFR 39.19. Directorate, Aircraft Certification Service. Office (telephone 1–800–647–5527), is
In accordance with 14 CFR 39.19, send your on the ground floor of the building at
[FR Doc. 2016–14301 Filed 6–20–16; 8:45 am]
request to your principal inspector or local
the above address.
Flight Standards District Office, as BILLING CODE 4910–13–P
appropriate. If sending information directly FAA Order 7400.9Z, Airspace
to the International Branch, send it to ATTN: Designations and Reporting Points, and
Sanjay Ralhan, Aerospace Engineer, subsequent amendments can be viewed
International Branch, ANM–116, Transport on line at http://www.faa.gov/airtraffic/
Airplane Directorate, FAA, 1601 Lind publications/. For further information,
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Document Created: 2016-06-21 01:30:39
Document Modified: 2016-06-21 01:30:39
| 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 August 5, 2016. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 81 FR 40210 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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