80_FR_74273 80 FR 74045 - Airworthiness Directives; Airbus Airplanes

80 FR 74045 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 228 (November 27, 2015)

Page Range74045-74047
FR Document2015-30023

We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A318, A319, and A320 series airplanes. This proposed AD was prompted by reports of an operator finding chafing damage on the fuselage skin at the bottom of certain frames, underneath the fairing structure. This proposed AD would require a repetitive detailed inspection for damage on the fuselage skin at certain frames, and applicable related investigative and corrective actions. We are proposing this AD to detect and correct damage to the fuselage skin, which could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage.

Federal Register, Volume 80 Issue 228 (Friday, November 27, 2015) 
[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)]
[Proposed Rules]
[Pages 74045-74047]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-30023]



[[Page 74045]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-5814; Directorate Identifier 2014-NM-247-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A318, A319, and A320 series airplanes. This 
proposed AD was prompted by reports of an operator finding chafing 
damage on the fuselage skin at the bottom of certain frames, underneath 
the fairing structure. This proposed AD would require a repetitive 
detailed inspection for damage on the fuselage skin at certain frames, 
and applicable related investigative and corrective actions. We are 
proposing this AD to detect and correct damage to the fuselage skin, 
which could lead to crack initiation and propagation, possibly 
resulting in reduced structural integrity of the fuselage.

DATES: We must receive comments on this proposed AD by January 11, 
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-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 account.airworth-eas@airbus.com; 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-
5814; 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-2015-5814; 
Directorate Identifier 2014-NM-247-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2014-0259, dated December 5, 2014 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A318, A319, and 
A320 series airplanes. The MCAI states:

    An operator reported finding chafing damage on the fuselage skin 
at the bottom of frame (FR) 34 junction between stringer (STR) 43 
left hand (LH) side and right hand (RH) side on several aeroplanes, 
underneath the fairing structure.
    After investigation, a contact between the fairing nut plate and 
the fuselage was identified, causing damage to the fuselage.
    This condition, if not detected and corrected, could lead to 
crack initiation and propagation, possibly resulting in reduced 
structural integrity of the fuselage.
    For the reason described above, this [EASA] AD requires 
repetitive detailed inspections (DET) of the fuselage [for chafing] 
at FR 34 and provides an optional terminating action [modification 
of the belly fairing] to the repetitive inspections required by this 
[EASA] AD.

    Related investigative actions include a special detailed inspection 
of external fuselage skin panel for any cracking, and measurement of 
crack length and remaining thickness. Corrective actions include repair 
or modification of the fuselage skin panel. You may examine the MCAI in 
the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-5814.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1281, Revision 01, dated 
December 1, 2014; and Service Bulletin A320-53-1287, dated July 29, 
2014. The service information describes procedures for a detailed 
inspection for damage (including chafing marks) on the fuselage skin at 
FR34 between STR43 LH and RH sides, and applicable related 
investigative and corrective actions. 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 these 
same type designs.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation

[[Page 74046]]

Rulemaking Committee (ARC), to enhance the AD system. One enhancement 
was a new process for annotating which procedures and tests in the 
service information are required for compliance with an AD. 
Differentiating these procedures and tests from other tasks in the 
service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The procedures and tests identified as 
Required for Compliance (RC) in any service information have a direct 
effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    As specified in a Note under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and 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 alternative method of compliance (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 will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 642 airplanes of U.S. 
registry.
    We also estimate that it would take about 12 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 $90 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $712,620, or $1,110 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 21 work-hours and require parts costing $3,550, for a cost 
of $5,335 per product. We have no way of determining the number of 
aircraft that might need this action.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-5814; Directorate Identifier 2014-NM-
247-AD.

(a) Comments Due Date

    We must receive comments by January 11, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers, except those on which Airbus 
Modification 37878 has been embodied in production, or Airbus 
Service Bulletin A320-53-1281 has been done in service.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of chafing damage on the 
fuselage skin at the bottom of certain frames, underneath the 
fairing structure. We are issuing this AD to detect and correct 
damage to the fuselage skin, which could lead to crack initiation 
and propagation, possibly resulting in reduced structural integrity 
of the fuselage.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspection and Corrective Action

    (1) Within the compliance times identified in paragraphs 
(g)(1)(i) and (g)(1)(ii) of this AD, whichever occurs later, do a 
detailed inspection for damage (including chafing marks) on the 
fuselage skin at frame (FR)34 between stringer (STR)43 on the left-
hand and right-hand sides, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1287, dated July 29, 
2014. Repeat the inspection thereafter at intervals not to exceed 
12,000 flight cycles or 24,000 flight hours, whichever occurs first.
    (i) Before exceeding 12,000 flight cycles or 24,000 flight 
hours, whichever occurs first since the airplane's first flight.
    (ii) Within 5,000 flight cycles or 10,000 flight hours, 
whichever occurs first after the effective date of this AD.
    (2) If any damage is detected during any inspection required by 
paragraph (g)(1) of this AD, before further flight, do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1287, dated July 29, 2014, except as required by 
paragraph (g)(3) of this AD.
    (3) If any cracking is found during any related investigative 
action required by paragraph (g)(2) of this AD, or if any damage 
detected during the inspection required by paragraph (g)(1) of this 
AD exceeds the limits defined in the Accomplishment Instructions

[[Page 74047]]

of Airbus Service Bulletin A320-53-1287, dated July 29, 2014, 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).

(h) Non-Terminating Repair Action

    Accomplishment of a repair on an airplane as required by 
paragraphs (g)(2) and (g)(3) of this AD, does not constitute 
terminating action for the repetitive detailed inspection required 
by paragraph (g)(1) of this AD, unless the approved repair indicates 
otherwise.

(i) Terminating Action for the Repetitive Detailed Inspection

    Modification of the belly fairing on any airplane in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1281, Revision 01, dated December 1, 2014, constitutes 
terminating action for the repetitive detailed inspection required 
by paragraph (g)(1) of this AD for that airplane.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(i) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A320-53-1281, dated 
July 29, 2014, which is not incorporated by reference in 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0259, dated December 5, 
2014, for related information.
    This MCAI may be found in the AD docket on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2015-5814.
    (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 account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on November 17, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-30023 Filed 11-25-15; 8:45 am]
 BILLING CODE 4910-13-P

Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74045 DEPARTMENT OF TRANSPORTATION SW., Renton, WA. For information on (STR) 43 left hand (LH) side and right hand the availability of this material at the (RH) side on several aeroplanes, underneath Federal Aviation Administration FAA, call 425–227–1221. the fairing structure. After investigation, a contact between the 14 CFR Part 39 Examining the AD Docket fairing nut plate and the fuselage was identified, causing damage to the fuselage. [Docket No. FAA–2015–5814; Directorate You may examine the AD docket on This condition, if not detected and Identifier 2014–NM–247–AD] the Internet at http:// corrected, could lead to crack initiation and www.regulations.gov by searching for propagation, possibly resulting in reduced RIN 2120–AA64 and locating Docket No. FAA–2015– structural integrity of the fuselage. 5814; or in person at the Docket For the reason described above, this Airworthiness Directives; Airbus Management Facility between 9 a.m. [EASA] AD requires repetitive detailed Airplanes and 5 p.m., Monday through Friday, inspections (DET) of the fuselage [for chafing] except Federal holidays. The AD docket at FR 34 and provides an optional AGENCY: Federal Aviation terminating action [modification of the belly Administration (FAA), DOT. contains this proposed AD, the fairing] to the repetitive inspections required ACTION: Notice of proposed rulemaking regulatory evaluation, any comments by this [EASA] AD. (NPRM). received, and other information. The street address for the Docket Operations Related investigative actions include a SUMMARY: We propose to adopt a new office (telephone 800–647–5527) is in special detailed inspection of external airworthiness directive (AD) for certain the ADDRESSES section. Comments will fuselage skin panel for any cracking, Airbus Model A318, A319, and A320 be available in the AD docket shortly and measurement of crack length and series airplanes. This proposed AD was after receipt. remaining thickness. Corrective actions prompted by reports of an operator include repair or modification of the FOR FURTHER INFORMATION CONTACT: finding chafing damage on the fuselage fuselage skin panel. You may examine Sanjay Ralhan, Aerospace Engineer, skin at the bottom of certain frames, the MCAI in the AD docket on the International Branch, ANM–116, underneath the fairing structure. This Internet at http://www.regulations.gov Transport Airplane Directorate, FAA, proposed AD would require a repetitive by searching for and locating Docket No. 1601 Lind Avenue SW., Renton, WA detailed inspection for damage on the FAA–2015–5814. 98057–3356; telephone 425–227–1405; fuselage skin at certain frames, and fax 425–227–1149. Related Service Information Under 1 applicable related investigative and SUPPLEMENTARY INFORMATION: CFR Part 51 corrective actions. We are proposing this AD to detect and correct damage to Comments Invited Airbus has issued Service Bulletin the fuselage skin, which could lead to A320–53–1281, Revision 01, dated We invite you to send any written December 1, 2014; and Service Bulletin crack initiation and propagation, relevant data, views, or arguments about possibly resulting in reduced structural A320–53–1287, dated July 29, 2014. The this proposed AD. Send your comments service information describes integrity of the fuselage. to an address listed under the procedures for a detailed inspection for DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No. damage (including chafing marks) on this proposed AD by January 11, 2016. FAA–2015–5814; Directorate Identifier the fuselage skin at FR34 between ADDRESSES: You may send comments, 2014–NM–247–AD’’ at the beginning of STR43 LH and RH sides, and applicable using the procedures found in 14 CFR your comments. We specifically invite related investigative and corrective 11.43 and 11.45, by any of the following comments on the overall regulatory, actions. This service information is methods: economic, environmental, and energy reasonably available because the • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will interested parties have access to it http://www.regulations.gov. Follow the consider all comments received by the through their normal course of business instructions for submitting comments. closing date and may amend this or by the means identified in the • Fax: 202–493–2251. proposed AD based on those comments. ADDRESSES section of this NPRM. • Mail: U.S. Department of We will post all comments we Transportation, Docket Operations, M– receive, without change, to http:// FAA’s Determination and Requirements 30, West Building Ground Floor, Room www.regulations.gov, including any of This Proposed AD W12–140, 1200 New Jersey Avenue SE., personal information you provide. We This product has been approved by Washington, DC 20590. will also post a report summarizing each the aviation authority of another • Hand Delivery: U.S. Department of substantive verbal contact we receive country, and is approved for operation Transportation, Docket Operations, M– about this proposed AD. in the United States. Pursuant to our 30, West Building Ground Floor, Room bilateral agreement with the State of Discussion W12–140, 1200 New Jersey Avenue SE., Design Authority, we have been notified Washington, DC, between 9 a.m. and 5 The European Aviation Safety Agency of the unsafe condition described in the p.m., Monday through Friday, except (EASA), which is the Technical Agent MCAI and service information Federal holidays. for the Member States of the European referenced above. We are proposing this For service information identified in Union, has issued EASA AD 2014–0259, AD because we evaluated all pertinent this proposed AD, contact Airbus, dated December 5, 2014 (referred to information and determined an unsafe Airworthiness Office—EIAS, 1 Rond after this as the Mandatory Continuing mstockstill on DSK4VPTVN1PROD with PROPOSALS condition exists and is likely to exist or Point Maurice Bellonte, 31707 Blagnac Airworthiness Information, or ‘‘the develop on other products of these same Cedex, France; telephone +33 5 61 93 36 MCAI’’), to correct an unsafe condition type designs. 96; fax +33 5 61 93 44 51; email for certain Airbus Model A318, A319, account.airworth-eas@airbus.com; and A320 series airplanes. The MCAI Explanation of ‘‘RC’’ Procedures and Internet http://www.airbus.com. You states: Tests in Service Information may view this referenced service An operator reported finding chafing The FAA worked in conjunction with information at the FAA, Transport damage on the fuselage skin at the bottom of industry, under the Airworthiness Airplane Directorate, 1601 Lind Avenue frame (FR) 34 junction between stringer Directive Implementation Aviation VerDate Sep<11>2014 16:45 Nov 25, 2015 Jkt 238001 PO 00000 Frm 00042 Fmt 4702 Sfmt 4702 E:\FR\FM\27NOP1.SGM 27NOP1

74046 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules Rulemaking Committee (ARC), to detail the scope of the Agency’s (a) Comments Due Date enhance the AD system. One authority. We must receive comments by January 11, enhancement was a new process for We are issuing this rulemaking under 2016. annotating which procedures and tests the authority described in ‘‘Subtitle VII, (b) Affected ADs in the service information are required Part A, Subpart III, Section 44701: None. for compliance with an AD. General requirements.’’ Under that Differentiating these procedures and section, Congress charges the FAA with (c) Applicability tests from other tasks in the service promoting safe flight of civil aircraft in This AD applies to the airplanes identified information is expected to improve an air commerce by prescribing regulations in paragraphs (c)(1), (c)(2), and (c)(3) of this owner’s/operator’s understanding of for practices, methods, and procedures AD, certificated in any category, all crucial AD requirements and help the Administrator finds necessary for manufacturer serial numbers, except those on provide consistent judgment in AD which Airbus Modification 37878 has been safety in air commerce. This regulation embodied in production, or Airbus Service compliance. The procedures and tests is within the scope of that authority Bulletin A320–53–1281 has been done in identified as Required for Compliance because it addresses an unsafe condition service. (RC) in any service information have a that is likely to exist or develop on (1) Airbus Model A318–111, –112, –121, direct effect on detecting, preventing, products identified in this rulemaking and –122 airplanes. resolving, or eliminating an identified action. (2) Airbus Model A319–111, –112, –113, unsafe condition. –114, –115, –131, –132, and –133 airplanes. As specified in a Note under the Regulatory Findings (3) Airbus Model A320–211, –212, –214, Accomplishment Instructions of the –231, –232, and –233 airplanes We determined that this proposed AD specified service information, would not have federalism implications (d) Subject procedures and tests that are identified under Executive Order 13132. This Air Transport Association (ATA) of as RC in any service information must proposed AD would not have a America Code 53, Fuselage. be done to comply with the proposed substantial direct effect on the States, on AD. However, procedures and tests that (e) Reason the relationship between the national are not identified as RC are Government and the States, or on the This AD was prompted by reports of recommended. Those procedures and chafing damage on the fuselage skin at the distribution of power and bottom of certain frames, underneath the tests that are not identified as RC may responsibilities among the various fairing structure. We are issuing this AD to be deviated from using accepted levels of government. detect and correct damage to the fuselage methods in accordance with the For the reasons discussed above, I skin, which could lead to crack initiation and operator’s maintenance or inspection certify this proposed regulation: propagation, possibly resulting in reduced program without obtaining approval of 1. Is not a ‘‘significant regulatory structural integrity of the fuselage. an alternative method of compliance action’’ under Executive Order 12866; (f) Compliance (AMOC), provided the procedures and 2. Is not a ‘‘significant rule’’ under the tests identified as RC can be done and Comply with this AD within the DOT Regulatory Policies and Procedures compliance times specified, unless already the airplane can be put back in an (44 FR 11034, February 26, 1979); done. airworthy condition. Any substitutions 3. Will not affect intrastate aviation in (g) Repetitive Inspection and Corrective or changes to procedures or tests Alaska; and Action identified as RC will require approval of 4. Will not have a significant an AMOC. (1) Within the compliance times identified economic impact, positive or negative, in paragraphs (g)(1)(i) and (g)(1)(ii) of this Costs of Compliance on a substantial number of small entities AD, whichever occurs later, do a detailed We estimate that this proposed AD under the criteria of the Regulatory inspection for damage (including chafing affects 642 airplanes of U.S. registry. Flexibility Act. marks) on the fuselage skin at frame (FR)34 We also estimate that it would take between stringer (STR)43 on the left-hand List of Subjects in 14 CFR Part 39 and right-hand sides, in accordance with the about 12 work-hours per product to Air transportation, Aircraft, Aviation Accomplishment Instructions of Airbus comply with the basic requirements of Service Bulletin A320–53–1287, dated July this proposed AD. The average labor safety, Incorporation by reference, 29, 2014. Repeat the inspection thereafter at rate is $85 per work-hour. Required Safety. intervals not to exceed 12,000 flight cycles or parts would cost about $90 per product. The Proposed Amendment 24,000 flight hours, whichever occurs first. Based on these figures, we estimate the (i) Before exceeding 12,000 flight cycles or cost of this proposed AD on U.S. Accordingly, under the authority 24,000 flight hours, whichever occurs first operators to be $712,620, or $1,110 per delegated to me by the Administrator, since the airplane’s first flight. the FAA proposes to amend 14 CFR part (ii) Within 5,000 flight cycles or 10,000 product. 39 as follows: flight hours, whichever occurs first after the In addition, we estimate that any effective date of this AD. necessary follow-on actions would take (2) If any damage is detected during any about 21 work-hours and require parts PART 39—AIRWORTHINESS DIRECTIVES inspection required by paragraph (g)(1) of costing $3,550, for a cost of $5,335 per this AD, before further flight, do all product. We have no way of applicable related investigative and ■ 1. The authority citation for part 39 corrective actions, in accordance with the determining the number of aircraft that continues to read as follows: Accomplishment Instructions of Airbus mstockstill on DSK4VPTVN1PROD with PROPOSALS might need this action. Authority: 49 U.S.C. 106(g), 40113, 44701. Service Bulletin A320–53–1287, dated July Authority for This Rulemaking 29, 2014, except as required by paragraph § 39.13 [Amended] (g)(3) of this AD. Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by adding (3) If any cracking is found during any specifies the FAA’s authority to issue related investigative action required by rules on aviation safety. Subtitle I, the following new airworthiness paragraph (g)(2) of this AD, or if any damage section 106, describes the authority of directive (AD): detected during the inspection required by the FAA Administrator. ‘‘Subtitle VII: Airbus: Docket No. FAA–2015–5814; paragraph (g)(1) of this AD exceeds the limits Aviation Programs,’’ describes in more Directorate Identifier 2014–NM–247–AD. defined in the Accomplishment Instructions VerDate Sep<11>2014 16:45 Nov 25, 2015 Jkt 238001 PO 00000 Frm 00043 Fmt 4702 Sfmt 4702 E:\FR\FM\27NOP1.SGM 27NOP1

Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74047 of Airbus Service Bulletin A320–53–1287, with this AD; any procedures or tests that are that the fuselage frames and frame dated July 29, 2014, before further flight, not identified as RC are recommended. Those reinforcements are subject to repair using a method approved by the procedures and tests that are not identified widespread fatigue damage (WFD). This Manager, International Branch, ANM–116, as RC may be deviated from using accepted proposed AD would add new inspection Transport Airplane Directorate, FAA; or the methods in accordance with the operator’s European Aviation Safety Agency (EASA); or maintenance or inspection program without areas, a modification that terminates Airbus’s EASA Design Organization obtaining approval of an AMOC, provided certain inspections, post-modification Approval (DOA). the procedures and tests identified as RC can inspections, and repair if necessary. We be done and the airplane can be put back in are proposing this AD to detect and (h) Non-Terminating Repair Action an airworthy condition. Any substitutions or correct fatigue cracking of the fuselage Accomplishment of a repair on an airplane changes to procedures or tests identified as frames and frame reinforcements, which as required by paragraphs (g)(2) and (g)(3) of RC require approval of an AMOC. could result in reduced structural this AD, does not constitute terminating (l) Related Information integrity of the airplane. action for the repetitive detailed inspection required by paragraph (g)(1) of this AD, (1) Refer to Mandatory Continuing DATES: We must receive comments on unless the approved repair indicates Airworthiness Information (MCAI) EASA this proposed AD by January 11, 2016. otherwise. Airworthiness Directive 2014–0259, dated ADDRESSES: You may send comments, December 5, 2014, for related information. using the procedures found in 14 CFR (i) Terminating Action for the Repetitive This MCAI may be found in the AD docket Detailed Inspection 11.43 and 11.45, by any of the following on the Internet at http://www.regulations.gov Modification of the belly fairing on any methods: by searching for and locating Docket No. airplane in accordance with the • Federal eRulemaking Portal: Go to FAA–2015–5814. Accomplishment Instructions of Airbus (2) For service information identified in http://www.regulations.gov. Follow the Service Bulletin A320–53–1281, Revision 01, this AD, contact Airbus, Airworthiness instructions for submitting comments. dated December 1, 2014, constitutes Office—EIAS, 1 Rond Point Maurice • Fax: 202–493–2251. terminating action for the repetitive detailed Bellonte, 31707 Blagnac Cedex, France; • Mail: U.S. Department of inspection required by paragraph (g)(1) of telephone +33 5 61 93 36 96; fax +33 5 61 Transportation, Docket Operations, M– this AD for that airplane. 93 44 51; email account.airworth-eas@ 30, West Building Ground Floor, Room airbus.com; Internet http://www.airbus.com. W12–140, 1200 New Jersey Avenue SE., (j) Credit for Previous Actions You may view this service information at the Washington, DC 20590. This paragraph provides credit for actions FAA, Transport Airplane Directorate, 1601 • Hand Delivery: Deliver to Mail required by paragraph (i) of this AD, if those Lind Avenue SW., Renton, WA. For actions were performed before the effective address above between 9 a.m. and 5 information on the availability of this date of this AD using Airbus Service Bulletin p.m., Monday through Friday, except material at the FAA, call 425–227–1221. A320–53–1281, dated July 29, 2014, which is Federal holidays. not incorporated by reference in this AD. Issued in Renton, Washington, on For service information identified in November 17, 2015. this proposed AD, contact Boeing (k) Other FAA AD Provisions Jeffrey E. Duven, Commercial Airplanes, Attention: Data The following provisions also apply to this Manager, Transport Airplane Directorate, & Services Management, P. O. Box 3707, AD: Aircraft Certification Service. MC 2H–65, Seattle, WA 98124–2207; (1) Alternative Methods of Compliance [FR Doc. 2015–30023 Filed 11–25–15; 8:45 am] telephone 206–544–5000, extension 1; (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane BILLING CODE 4910–13–P fax 206–766–5680; Internet https:// Directorate, FAA, has the authority to www.myboeingfleet.com. You may view approve AMOCs for this AD, if requested this referenced service information at using the procedures found in 14 CFR 39.19. DEPARTMENT OF TRANSPORTATION the FAA, Transport Airplane In accordance with 14 CFR 39.19, send your Directorate, 1601 Lind Avenue SW., request to your principal inspector or local Federal Aviation Administration Renton, Washington. For information on Flight Standards District Office, as the availability of this material at the appropriate. If sending information directly 14 CFR Part 39 FAA, call 425–227–1221. It is also to the International Branch, send it to ATTN: [Docket No. FAA–2015–5812; Directorate available on the Internet at http:// Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Identifier 2015–NM–077–AD] www.regulations.gov by searching for Airplane Directorate, FAA, 1601 Lind and locating Docket No. FAA–2015– RIN 2120–AA64 5812. Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Airworthiness Directives; The Boeing Examining the AD Docket Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using Company Airplanes You may examine the AD docket on any approved AMOC, notify your appropriate AGENCY: Federal Aviation the Internet at http:// principal inspector, or lacking a principal Administration (FAA), DOT. www.regulations.gov by searching for inspector, the manager of the local flight and locating Docket No. FAA–2015– standards district office/certificate holding ACTION: Notice of proposed rulemaking (NPRM). 5812; or in person at the Docket district office. The AMOC approval letter must specifically reference this AD. Management Facility between 9 a.m. (2) Contacting the Manufacturer: For any SUMMARY: We propose to supersede and 5 p.m., Monday through Friday, requirement in this AD to obtain corrective Airworthiness Directive (AD) 2011–23– except Federal holidays. The AD docket actions from a manufacturer, the action must 05, which applies to certain The Boeing contains this proposed AD, the be accomplished using a method approved Company Model 737–300, –400, and regulatory evaluation, any comments mstockstill on DSK4VPTVN1PROD with PROPOSALS by the Manager, International Branch, ANM– –500 series airplanes. AD 2011–23–05 received, and other information. The 116, Transport Airplane Directorate, FAA; or currently requires repetitive inspections street address for the Docket Office the EASA; or Airbus’s EASA DOA. If for cracking of the 1.04-inch nominal (phone: 800–647–5527) is in the approved by the DOA, the approval must ADDRESSES section. Comments will be include the DOA-authorized signature. diameter wire penetration hole, and (3) Required for Compliance (RC): If any applicable related investigative and available in the AD docket shortly after service information contains procedures or corrective actions. Since we issued AD receipt. tests that are identified as RC, those 2011–23–05, an evaluation by the FOR FURTHER INFORMATION CONTACT: procedures and tests must be done to comply design approval holder (DAH) indicates Wayne Lockett, Aerospace Engineer, VerDate Sep<11>2014 16:45 Nov 25, 2015 Jkt 238001 PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 E:\FR\FM\27NOP1.SGM 27NOP1


Document Created: 2015-12-14 14:05:06
Document Modified: 2015-12-14 14:05:06
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by January 11, 2016.
ContactSanjay 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 Citation80 FR 74045 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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