Document ID: FAA-2016-7262-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-06-21T04:00Z

[Federal Register Volume 81, Number 119 (Tuesday, June 21, 2016)]
[Proposed Rules]
[Pages 40210-40213]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-14301]

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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).

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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 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-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: 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.

(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 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 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