80 FR 32055 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 108 (June 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 108 (June 5, 2015)
| Page Range | 32055-32057 | |
| FR Document | 2015-13340 |
[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)] [Proposed Rules] [Pages 32055-32057] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-13340] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1427; Directorate Identifier 2013-NM-203-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) 96-18-06 for certain Airbus Model A320-211 and -231 airplanes. AD 96-18-06 currently requires visual inspections to detect cracks of the pressurized floor fittings at frame (FR) 36, and renewal of the zone protective finish or replacement of fittings with new fittings if necessary. Since we issued AD 96-18-06, an extended service goal analysis by the manufacturer revealed that the compliance times and repetitive inspection intervals should be reduced to meet the design service goal. This proposed AD would retain the requirements of AD 96- 18-06, with reduced compliance times and repetitive inspection intervals. This proposed AD would also add Model A320-212 airplanes to the applicability. We are proposing this AD to detect and correct fatigue cracking in the pressurized floor fittings at FR 36, which could result in failure of a floor fitting and subsequent depressurization of the fuselage. DATES: We must receive comments on this proposed AD by July 20, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: (202) 493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1427; 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-2015-1427; Directorate Identifier 2013-NM-203-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On August 23, 1996, we issued AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996). AD 96-18-06 requires actions intended to address an unsafe condition on certain Airbus Model A320-211 and -231 airplanes. Since we issued AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996), an extended service goal analysis by the manufacturer revealed that the compliance times and repetitive inspection intervals must be reduced to meet the design service goal. The European Aviation Safety Agency (EASA), which is the Technical Agency for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0226, dated September 23, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for Airbus Model A320- 211, -212, and -231 airplanes. The MCAI states: During center fuselage certification full scale fatigue test, damage was found on the pressurized floor fittings at Frame 36, below the lower surface panel. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To prevent such damage, Airbus developed modification 21282, which was introduced in production from [manufacturer serial number] MSN 0105, to reinforce the pressurized floor fitting lower surface by changing material. For affected in-service aeroplanes, Airbus issued Service Bulletin (SB) A320-57-1028, introducing repetitive inspections, and SB A320-57-1029, which provides modification instructions. DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued [an] AD * * * [for Model A320-111, -211, and -231 airplanes] to require these repetitive inspections and, depending on findings, corrective action(s), while the modification was specified in that AD as optional terminating action for these inspections. Following new analysis in the frame of ESG (Extended Service Goal) exercise, the inspection thresholds and intervals have been revised to meet the original DSG (Design Service Goal). [[Page 32056]] For the reasons described above, this [EASA] AD retains the requirements of [a] DGAC France AD * * *, which is superseded, but requires these actions within reduced compliance times. [This EASA AD also adds Model A320-212 airplanes to its applicability.] You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA- 2015-1427. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. The service information describes procedures for an inspection to detect cracks of the pressurized floor fittings at frame (FR) 36, renewal of the zone protective finish, and replacement of fittings with new fittings. Airbus has also issued Service Bulletin A320-57-1029, Revision 02, dated June 16, 1999. The service information describes procedures for modification of the pressurized floor fittings at FR 36. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Unlike the required actions in the MCAI, this proposed AD would not permit further flight if damage (cracking) is detected during any inspection of the pressurized floor fittings at FR 36. Instead, this proposed AD would require repair of any damage before further flight. We find that, to achieve an adequate level of safety for the affected fleet, damaged structural elements must be replaced prior to further flight. This difference has been coordinated with EASA. Costs of Compliance We estimate that this proposed AD affects 13 airplanes of U.S. registry. The actions required by AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996), and retained in this proposed AD, take about 3 work-hours per product, at an average labor rate of $85 per work- hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 96-18-06 is $255 per product. We also estimate that it would take about 11 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 $0 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $12,155, or $935 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) 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996), and adding the following new AD: Airbus: Docket No. FAA-2015-1427; Directorate Identifier 2013-NM- 203-AD. (a) Comments Due Date We must receive comments by July 20, 2015. (b) Affected ADs This AD replaces AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996). (c) Applicability This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers 0002 through 0104 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by an extended service goal analysis by the manufacturer, which revealed that the compliance times and repetitive inspection intervals should be reduced to meet the design service goal. We are issuing this AD to detect and correct fatigue cracking in the pressurized floor fittings at FR 36, which could result in failure of a floor fitting and subsequent depressurization of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. [[Page 32057]] (g) Retained Inspection This paragraph restates the requirements of paragraph (a) of AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996), with revised service information for Airbus Model A320-211 and -231 airplanes. Prior to the accumulation of 16,000 total landings, or within 6 months after October 10, 1996 (the effective date of AD 96- 18-06), whichever occurs later, perform a visual inspection to detect cracks of the 6 fittings of the pressurized floor at frame 36 under the lower surface panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. Accomplishment of the initial inspection required by paragraph (i) of this AD terminates the actions required by this paragraph. (1) If no cracking is found, prior to further flight, renew the zone protective finish, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. Repeat the visual inspection thereafter at intervals not to exceed 12,000 landings. (2) If only 1 of the 6 fittings is found to be cracked and that crack is less than or equal to 0.59 inch (15 mm) in length, prior to further flight, replace the cracked fitting with a new fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. Thereafter, prior to the accumulation of 500 landings following accomplishment of this replacement, replace the remaining 5 fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. (3) If only 1 of the 6 fittings is found to be cracked, and that crack is greater than 0.59 inch (15 mm) in length, prior to further flight, replace all six fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57- 1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. (4) If 2 or more fittings are found to be cracked, prior to further flight, replace all 6 fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 1, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. As of the effective date of this AD, use only Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013, for accomplishing the actions required by this paragraph. (h) Retained Optional Terminating Action This paragraph restates the provisions of paragraph (b) of AD 96-18-06, Amendment 39-9730 (61 FR 46703, September 5, 1996), with revised service information for Airbus Model A320-211 and -231 airplanes. Replacement of all 6 fittings with new fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 01, dated April 19, 1996; or Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013; constitutes terminating action for the inspection requirements of paragraph (g) of this AD. (i) New Inspection (1) At the latest of the times in paragraph (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD: Do a detailed inspection of the pressurized floor fittings at frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1028, Revision 02, dated June 3, 2013. Repeat the inspection thereafter, at intervals not to exceed 9,300 flight cycles or 18,600 flight hours, whichever occurs first. Accomplishment of the initial inspection required by this paragraph terminates the actions required by paragraph (g) of this AD. (i) Prior to the accumulation of 20,900 total flight cycles or 41,800 total flight hours, whichever occurs first. (ii) Prior to the accumulation of 9,300 flight cycles or 18,600 flight cycles since the most recent inspection required by paragraph (g) or (i) of this AD, whichever occurs first. (iii) At the earlier of the times specified in paragraph (i)(iii)(A) and (i)(iii)(B) of this AD. (A) Prior to the accumulation of 1,250 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. (B) Prior to the accumulation of 12,000 flight cycles since the most recent inspection required by paragraph (g) or (i) of this AD. (2) If any crack is found during any inspection required by paragraph (i)(1) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (j) New Optional Terminating Action Modification (replacement of aluminum fittings with titanium fittings) of the pressurized floor fittings at frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1029, Revision 02, dated June 16, 1999, is terminating action for the repetitive inspections required by paragraphs (g) and (i) of this AD. (k) 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 for AD 96-18-06, Amendment 39- 9730 (61 FR 46703, September 5, 1996), are approved as AMOCs for the corresponding provisions 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0226, dated September 23, 2013, 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-2015-1427. (2) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on May 19, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-13340 Filed 6-4-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32055
fitting and subsequent depressurization ADDRESSES section. Include ‘‘Docket No.
Dated: May 27, 2015. of the fuselage. FAA–2015–1427; Directorate Identifier
Thomas J. Curry, DATES: We must receive comments on 2013–NM–203–AD’’ at the beginning of
this proposed AD by July 20, 2015. your comments. We specifically invite
Comptroller of the Currency.
ADDRESSES: You may send comments by comments on the overall regulatory,
By order of the Board of Governors of the
any of the following methods: economic, environmental, and energy
Federal Reserve System, May 29, 2015. aspects of this proposed AD. We will
• Federal eRulemaking Portal: Go to
Michael Lewandowski, http://www.regulations.gov. Follow the consider all comments received by the
Associate Secretary of the Board. instructions for submitting comments. closing date and may amend this
Dated: May 29, 2015. • Fax: (202) 493–2251. proposed AD based on those comments.
By order of the Board of Directors. • Mail: U.S. Department of We will post all comments we
Federal Deposit Insurance Corporation. Transportation, Docket Operations, M– receive, without change, to http://
Robert E. Feldman, 30, West Building Ground Floor, Room www.regulations.gov, including any
W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
Executive Secretary.
Washington, DC 20590. will also post a report summarizing each
[FR Doc. 2015–13749 Filed 6–4–15; 8:45 am]
• Hand Delivery: U.S. Department of substantive verbal contact we receive
BILLING CODE P about this proposed AD.
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room Discussion
W12–140, 1200 New Jersey Avenue SE., On August 23, 1996, we issued AD
DEPARTMENT OF TRANSPORTATION
Washington, DC, between 9 a.m. and 5 96–18–06, Amendment 39–9730 (61 FR
Federal Aviation Administration p.m., Monday through Friday, except 46703, September 5, 1996). AD 96–18–
Federal holidays. 06 requires actions intended to address
14 CFR Part 39 For service information identified in an unsafe condition on certain Airbus
this proposed AD, contact Airbus, Model A320–211 and –231 airplanes.
[Docket No. FAA–2015–1427; Directorate Airworthiness Office—EIAS, 1 Rond
Identifier 2013–NM–203–AD] Since we issued AD 96–18–06,
Point Maurice Bellonte, 31707 Blagnac Amendment 39–9730 (61 FR 46703,
RIN 2120–AA64 Cedex, France; telephone +33 5 61 93 36 September 5, 1996), an extended service
96; fax +33 5 61 93 44 51; email goal analysis by the manufacturer
Airworthiness Directives; Airbus account.airworth-eas@airbus.com; revealed that the compliance times and
Airplanes Internet http://www.airbus.com. You repetitive inspection intervals must be
may view this referenced service reduced to meet the design service goal.
AGENCY: Federal Aviation information at the FAA, Transport
Administration (FAA), DOT. The European Aviation Safety Agency
Airplane Directorate, 1601 Lind Avenue (EASA), which is the Technical Agency
ACTION: Notice of proposed rulemaking SW., Renton, WA. For information on for the Member States of the European
(NPRM). the availability of this material at the Union, has issued EASA Airworthiness
FAA, call 425–227–1221. Directive 2013–0226, dated September
SUMMARY: We propose to supersede
Airworthiness Directive (AD) 96–18–06 Examining the AD Docket 23, 2013 (referred to after this as the
for certain Airbus Model A320–211 and Mandatory Continuing Airworthiness
You may examine the AD docket on Information, or ‘‘the MCAI’’), to correct
–231 airplanes. AD 96–18–06 currently the Internet at http://
requires visual inspections to detect an unsafe condition for Airbus Model
www.regulations.gov by searching for A320–211, –212, and –231 airplanes.
cracks of the pressurized floor fittings at and locating Docket No. FAA–2015–
frame (FR) 36, and renewal of the zone The MCAI states:
1427; or in person at the Docket
protective finish or replacement of During center fuselage certification full
Management Facility between 9 a.m.
fittings with new fittings if necessary. scale fatigue test, damage was found on the
and 5 p.m., Monday through Friday, pressurized floor fittings at Frame 36, below
Since we issued AD 96–18–06, an except Federal holidays. The AD docket the lower surface panel. This condition, if
extended service goal analysis by the contains this proposed AD, the not detected and corrected, could affect the
manufacturer revealed that the regulatory evaluation, any comments structural integrity of the aeroplane.
compliance times and repetitive received, and other information. The To prevent such damage, Airbus developed
inspection intervals should be reduced street address for the Docket Operations modification 21282, which was introduced in
to meet the design service goal. This office (telephone (800) 647–5527) is in production from [manufacturer serial
proposed AD would retain the number] MSN 0105, to reinforce the
the ADDRESSES section. Comments will pressurized floor fitting lower surface by
requirements of AD 96–18–06, with be available in the AD docket shortly changing material. For affected in-service
reduced compliance times and after receipt. aeroplanes, Airbus issued Service Bulletin
repetitive inspection intervals. This (SB) A320–57–1028, introducing repetitive
FOR FURTHER INFORMATION CONTACT:
proposed AD would also add Model inspections, and SB A320–57–1029, which
Sanjay Ralhan, Aerospace Engineer,
A320–212 airplanes to the applicability. provides modification instructions.
International Branch, ANM–116,
We are proposing this AD to detect and DGAC [Direction Générale de l’Aviation
Transport Airplane Directorate, FAA, Civile] France issued [an] AD * * * [for
correct fatigue cracking in the
1601 Lind Avenue SW., Renton, WA
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
pressurized floor fittings at FR 36, Model A320–111, –211, and –231 airplanes]
98057–3356; telephone 425–227–1405; to require these repetitive inspections and,
which could result in failure of a floor
fax 425–227–1149. depending on findings, corrective action(s),
9 Regulations for which rulemaking authority has SUPPLEMENTARY INFORMATION: while the modification was specified in that
AD as optional terminating action for these
transferred to the CFPB are not included in this
Consumer Protection category. As described in the
Comments Invited inspections.
Supplementary Information section of this notice, Following new analysis in the frame of
We invite you to send any written ESG (Extended Service Goal) exercise, the
the CFPB is required to review its significant rules
and publish a report of its review no later than five
relevant data, views, or arguments about inspection thresholds and intervals have
years after they take effect, in a process separate this proposed AD. Send your comments been revised to meet the original DSG
from the EGRPRA process. to an address listed under the (Design Service Goal).
VerDate Sep<11>2014 19:05 Jun 04, 2015 Jkt 235001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 E:\FR\FM\05JNP1.SGM 05JNP1](https://thefederalregister.org/doc/80_FR_32163/page/1.svg)
![32056 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules
For the reasons described above, this Costs of Compliance 2. Is not a ‘‘significant rule’’ under the
[EASA] AD retains the requirements of [a] DOT Regulatory Policies and Procedures
DGAC France AD * * *, which is We estimate that this proposed AD
affects 13 airplanes of U.S. registry. (44 FR 11034, February 26, 1979);
superseded, but requires these actions within 3. Will not affect intrastate aviation in
reduced compliance times. [This EASA AD The actions required by AD 96–18–06,
Alaska; and
also adds Model A320–212 airplanes to its Amendment 39–9730 (61 FR 46703,
applicability.]
4. Will not have a significant
September 5, 1996), and retained in this
economic impact, positive or negative,
You may examine the MCAI in the AD proposed AD, take about 3 work-hours
on a substantial number of small entities
docket on the Internet at http:// per product, at an average labor rate of
under the criteria of the Regulatory
www.regulations.gov by searching for $85 per work-hour. Required parts cost
Flexibility Act.
and locating it in Docket No. FAA– about $0 per product. Based on these
2015–1427. figures, the estimated cost of the actions List of Subjects in 14 CFR Part 39
that are required by AD 96–18–06 is Air transportation, Aircraft, Aviation
Related Service Information Under 1 $255 per product. safety, Incorporation by reference,
CFR Part 51 We also estimate that it would take Safety.
Airbus has issued Service Bulletin about 11 work-hours per product to
comply with the basic requirements of The Proposed Amendment
A320–57–1028, Revision 02, dated June
3, 2013. The service information this proposed AD. The average labor Accordingly, under the authority
describes procedures for an inspection rate is $85 per work-hour. Required delegated to me by the Administrator,
to detect cracks of the pressurized floor parts would cost about $0 per product. the FAA proposes to amend 14 CFR part
fittings at frame (FR) 36, renewal of the Based on these figures, we estimate the 39 as follows:
zone protective finish, and replacement cost of this proposed AD on U.S.
of fittings with new fittings. operators to be $12,155, or $935 per PART 39—AIRWORTHINESS
product. DIRECTIVES
Airbus has also issued Service We have received no definitive data
Bulletin A320–57–1029, Revision 02, that would enable us to provide cost ■ 1. The authority citation for part 39
dated June 16, 1999. The service estimates for the on-condition actions continues to read as follows:
information describes procedures for specified in this proposed AD. Authority: 49 U.S.C. 106(g), 40113, 44701.
modification of the pressurized floor
fittings at FR 36. Authority for This Rulemaking § 39.13 [Amended]
The actions described in this service Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
information are intended to correct the specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
unsafe condition identified in the rules on aviation safety. Subtitle I, 96–18–06, Amendment 39–9730 (61 FR
MCAI. This service information is section 106, describes the authority of 46703, September 5, 1996), and adding
reasonably available because the the FAA Administrator. ‘‘Subtitle VII: the following new AD:
interested parties have access to it Aviation Programs,’’ describes in more Airbus: Docket No. FAA–2015–1427;
through their normal course of business detail the scope of the Agency’s Directorate Identifier 2013–NM–203–AD.
or by the means identified in the authority.
ADDRESSES section of this NPRM. (a) Comments Due Date
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII, We must receive comments by July 20,
FAA’s Determination and Requirements 2015.
of This Proposed AD Part A, Subpart III, Section 44701:
General requirements.’’ Under that (b) Affected ADs
This product has been approved by section, Congress charges the FAA with This AD replaces AD 96–18–06,
the aviation authority of another promoting safe flight of civil aircraft in Amendment 39–9730 (61 FR 46703,
country, and is approved for operation air commerce by prescribing regulations September 5, 1996).
in the United States. Pursuant to our for practices, methods, and procedures
bilateral agreement with the State of (c) Applicability
the Administrator finds necessary for
Design Authority, we have been notified safety in air commerce. This regulation This AD applies to Airbus Model A320–
of the unsafe condition described in the 211, –212, and –231 airplanes, certificated in
is within the scope of that authority any category, manufacturer serial numbers
MCAI and service information because it addresses an unsafe condition 0002 through 0104 inclusive.
referenced above. We are proposing this that is likely to exist or develop on
AD because we evaluated all pertinent products identified in this rulemaking (d) Subject
information and determined an unsafe action. Air Transport Association (ATA) of
condition exists and is likely to exist or America Code 57, Wings.
develop on other products of the same Regulatory Findings
(e) Reason
type design. We determined that this proposed AD
This AD was prompted by an extended
Unlike the required actions in the would not have federalism implications service goal analysis by the manufacturer,
MCAI, this proposed AD would not under Executive Order 13132. This which revealed that the compliance times
permit further flight if damage proposed AD would not have a and repetitive inspection intervals should be
(cracking) is detected during any substantial direct effect on the States, on reduced to meet the design service goal. We
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
inspection of the pressurized floor the relationship between the national are issuing this AD to detect and correct
fittings at FR 36. Instead, this proposed Government and the States, or on the fatigue cracking in the pressurized floor
AD would require repair of any damage distribution of power and fittings at FR 36, which could result in failure
before further flight. We find that, to responsibilities among the various of a floor fitting and subsequent
achieve an adequate level of safety for levels of government. depressurization of the fuselage.
the affected fleet, damaged structural For the reasons discussed above, I (f) Compliance
elements must be replaced prior to certify this proposed regulation: Comply with this AD within the
further flight. This difference has been 1. Is not a ‘‘significant regulatory compliance times specified, unless already
coordinated with EASA. action’’ under Executive Order 12866; done.
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![Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32057
(g) Retained Inspection the Accomplishment Instructions of Airbus (k) Other FAA AD Provisions
This paragraph restates the requirements of Service Bulletin A320–57–1028, Revision 1, The following provisions also apply to this
paragraph (a) of AD 96–18–06, Amendment dated April 19, 1996; or Airbus Service AD:
39–9730 (61 FR 46703, September 5, 1996), Bulletin A320–57–1028, Revision 02, dated (1) Alternative Methods of Compliance
with revised service information for Airbus June 3, 2013. As of the effective date of this (AMOCs): The Manager, International
Model A320–211 and –231 airplanes. Prior to AD, use only Airbus Service Bulletin A320– Branch, ANM–116, Transport Airplane
the accumulation of 16,000 total landings, or 57–1028, Revision 02, dated June 3, 2013, for Directorate, FAA, has the authority to
within 6 months after October 10, 1996 (the accomplishing the actions required by this approve AMOCs for this AD, if requested
effective date of AD 96–18–06), whichever paragraph. using the procedures found in 14 CFR 39.19.
occurs later, perform a visual inspection to In accordance with 14 CFR 39.19, send your
(h) Retained Optional Terminating Action
detect cracks of the 6 fittings of the request to your principal inspector or local
pressurized floor at frame 36 under the lower This paragraph restates the provisions of
Flight Standards District Office, as
surface panel, in accordance with the paragraph (b) of AD 96–18–06, Amendment
39–9730 (61 FR 46703, September 5, 1996), appropriate. If sending information directly
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1028, Revision 1, with revised service information for Airbus to the International Branch, send it to ATTN:
dated April 19, 1996; or Airbus Service Model A320–211 and –231 airplanes. Sanjay Ralhan, Aerospace Engineer,
Bulletin A320–57–1028, Revision 02, dated Replacement of all 6 fittings with new International Branch, ANM–116, Transport
June 3, 2013. As of the effective date of this fittings, in accordance with the Airplane Directorate, FAA, 1601 Lind
AD, use only Airbus Service Bulletin A320– Accomplishment Instructions of Airbus Avenue SW., Renton, WA 98057–3356;
57–1028, Revision 02, dated June 3, 2013, for Service Bulletin A320–57–1028, Revision 01, telephone 425–227–1405; fax 425–227–1149.
accomplishing the actions required by this dated April 19, 1996; or Airbus Service Information may be emailed to: 9-ANM-116-
paragraph. Accomplishment of the initial Bulletin A320–57–1028, Revision 02, dated AMOC-REQUESTS@faa.gov.
inspection required by paragraph (i) of this June 3, 2013; constitutes terminating action (i) Before using any approved AMOC,
AD terminates the actions required by this for the inspection requirements of paragraph notify your appropriate principal inspector,
paragraph. (g) of this AD. or lacking a principal inspector, the manager
(1) If no cracking is found, prior to further of the local flight standards district office/
flight, renew the zone protective finish, in (i) New Inspection certificate holding district office. The AMOC
accordance with the Accomplishment (1) At the latest of the times in paragraph approval letter must specifically reference
Instructions of Airbus Service Bulletin A320– (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD: Do this AD.
57–1028, Revision 1, dated April 19, 1996; or a detailed inspection of the pressurized floor (ii) AMOCs approved previously for AD
Airbus Service Bulletin A320–57–1028, fittings at frame 36, in accordance with the 96–18–06, Amendment 39–9730 (61 FR
Revision 02, dated June 3, 2013. As of the Accomplishment Instructions of Airbus 46703, September 5, 1996), are approved as
effective date of this AD, use only Airbus AMOCs for the corresponding provisions of
Service Bulletin A320–57–1028, Revision 02,
Service Bulletin A320–57–1028, Revision 02, this AD.
dated June 3, 2013. Repeat the inspection
dated June 3, 2013, for accomplishing the
thereafter, at intervals not to exceed 9,300 (2) Contacting the Manufacturer: As of the
actions required by this paragraph. Repeat
flight cycles or 18,600 flight hours, effective date of this AD, for any requirement
the visual inspection thereafter at intervals
whichever occurs first. Accomplishment of in this AD to obtain corrective actions from
not to exceed 12,000 landings.
(2) If only 1 of the 6 fittings is found to be the initial inspection required by this a manufacturer, the action must be
cracked and that crack is less than or equal paragraph terminates the actions required by accomplished using a method approved by
to 0.59 inch (15 mm) in length, prior to paragraph (g) of this AD. the Manager, International Branch, ANM–
further flight, replace the cracked fitting with (i) Prior to the accumulation of 20,900 total 116, Transport Airplane Directorate, FAA; or
a new fitting, in accordance with the flight cycles or 41,800 total flight hours, the EASA; or Airbus’s EASA DOA. If
Accomplishment Instructions of Airbus whichever occurs first. approved by the DOA, the approval must
Service Bulletin A320–57–1028, Revision 1, (ii) Prior to the accumulation of 9,300 flight include the DOA-authorized signature.
dated April 19, 1996; or Airbus Service cycles or 18,600 flight cycles since the most
recent inspection required by paragraph (g) (l) Related Information
Bulletin A320–57–1028, Revision 02, dated
June 3, 2013. Thereafter, prior to the or (i) of this AD, whichever occurs first. (1) Refer to Mandatory Continuing
accumulation of 500 landings following (iii) At the earlier of the times specified in Airworthiness Information (MCAI) EASA
accomplishment of this replacement, replace paragraph (i)(iii)(A) and (i)(iii)(B) of this AD. Airworthiness Directive 2013–0226, dated
the remaining 5 fittings with new fittings, in (A) Prior to the accumulation of 1,250 September 23, 2013, for related information.
accordance with the Accomplishment flight cycles or 2,500 flight hours after the This MCAI may be found in the AD docket
Instructions of Airbus Service Bulletin A320– effective date of this AD, whichever occurs on the Internet at http://www.regulations.gov
57–1028, Revision 1, dated April 19, 1996; or first. by searching for and locating Docket No.
Airbus Service Bulletin A320–57–1028, (B) Prior to the accumulation of 12,000 FAA–2015–1427.
Revision 02, dated June 3, 2013. As of the flight cycles since the most recent inspection (2) For service information identified in
effective date of this AD, use only Airbus required by paragraph (g) or (i) of this AD. this AD, contact Airbus, Airworthiness
Service Bulletin A320–57–1028, Revision 02, (2) If any crack is found during any Office—EIAS, 1 Rond Point Maurice
dated June 3, 2013, for accomplishing the inspection required by paragraph (i)(1) of this Bellonte, 31707 Blagnac Cedex, France;
actions required by this paragraph. AD: Before further flight, repair using a telephone +33 5 61 93 36 96; fax +33 5 61
(3) If only 1 of the 6 fittings is found to be method approved by the Manager, 93 44 51; email account.airworth-eas@
cracked, and that crack is greater than 0.59 International Branch, ANM–116, Transport airbus.com; Internet http://www.airbus.com.
inch (15 mm) in length, prior to further flight, Airplane Directorate, FAA; or the European
You may view this service information at the
replace all six fittings with new fittings, in Aviation Safety Agency (EASA); or Airbus’s
FAA, Transport Airplane Directorate, 1601
accordance with the Accomplishment EASA Design Organization Approval (DOA).
Lind Avenue SW., Renton, WA. For
Instructions of Airbus Service Bulletin A320–
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(j) New Optional Terminating Action information on the availability of this
57–1028, Revision 1, dated April 19, 1996; or
Modification (replacement of aluminum material at the FAA, call 425–227–1221.
Airbus Service Bulletin A320–57–1028,
Revision 02, dated June 3, 2013. As of the fittings with titanium fittings) of the Issued in Renton, Washington, on May 19,
effective date of this AD, use only Airbus pressurized floor fittings at frame 36, in 2015.
Service Bulletin A320–57–1028, Revision 02, accordance with the Accomplishment Dionne Palermo,
dated June 3, 2013, for accomplishing the Instructions of Airbus Service Bulletin A320–
57–1029, Revision 02, dated June 16, 1999, Acting Manager, Transport Airplane
actions required by this paragraph.
is terminating action for the repetitive Directorate, Aircraft Certification Service.
(4) If 2 or more fittings are found to be
cracked, prior to further flight, replace all 6 inspections required by paragraphs (g) and (i) [FR Doc. 2015–13340 Filed 6–4–15; 8:45 am]
fittings with new fittings, in accordance with of this AD. BILLING CODE 4910–13–P
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Document Created: 2015-12-15 15:20:53
Document Modified: 2015-12-15 15:20:53
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by July 20, 2015. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 80 FR 32055 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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