Document ID: FAA-2017-0695-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2018-03-15T04:00Z

[Federal Register Volume 83, Number 51 (Thursday, March 15, 2018)]
[Rules and Regulations]
[Pages 11399-11404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-05018]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0695; Product Identifier 2016-NM-173-AD; Amendment 
39-19223; AD 2018-06-03]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2009-18-16, 
which applied to certain Airbus Model A310-203, -204, -221, -222, -304, 
-322, -324, and -325 airplanes. AD 2009-18-16 required an inspection 
for cracking of certain fastener holes on certain frames, and related 
investigative and corrective actions if necessary; and modification of 
certain fastener holes. This new AD reduces the compliance times. This 
AD was prompted by the identification of a structural modification that 
falls within the scope of the work related to the extension of the 
service life of the affected airplanes and widespread fatigue damage 
evaluations. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective April 19, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 19, 
2018.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 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 Standards Branch, 2200

[[Page 11400]]

South 216th St., Des Moines, WA. For information on the availability of 
this material at the FAA, call 206-231-3195. It is also available on 
the internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2017-0695.

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-2017-
0695; 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone 206-231-3225.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2009-18-16, Amendment 39-16012 (74 FR 46342, 
September 9, 2009) (``AD 2009-18-16''). AD 2009-18-16 applied to 
certain Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and 
-325 airplanes. The NPRM published in the Federal Register on July 14, 
2017 (82 FR 32503). We are issuing this AD to prevent fatigue cracking 
of the frame foot run-outs, which could lead to rupture of the frame 
foot and cracking in adjacent frames and skin, and which could result 
in reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0197, dated October 5, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), for 
all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes. EASA AD 2016-0197 supersedes EASA AD 2008-0212, dated 
December 4, 2008. EASA AD 2008-0212 was the MCAI referred to in FAA AD 
2009-18-16. The new MCAI states:

    Within the scope of work related to the extension of the service 
life of A310 design and widespread fatigue damage evaluations, DGAC 
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France 
issued AD F-2005-078 (EASA approval 2005-3957) [which corresponds to 
FAA AD 2006-02-06, Amendment 39-14458 (71 FR 3214, January 20, 
2006)] to require a structural modification, as defined in Airbus 
Service Bulletin (SB) A310-53-2124 (Airbus modification 13023), to 
increase the service life of junctions of center box upper frame 
bases to upper fuselage arches.
    The threshold timescales for accomplishment of the tasks as 
defined in SB A310-53-2124 were refined and reduced. Consequently, 
EASA issued AD 2007-0238 to require compliance with Revision 01 of 
SB A310-53-2124 at the reduced compliance times, superseding (the 
requirements of) DGAC France AD F-2005-078. Subsequently, Airbus 
identified reference material that was erroneously introduced into 
Airbus SB A310-53-2124 Revision 01. As a result, the SB instructions 
could not be accomplished properly. Operators that tried to apply SB 
A310-53-2124 at Revision 01 had to contact Airbus; see also Airbus 
SBIT [service bulletin information telex] ref. 914.0135/08, dated 03 
March 2008.
    Consequently, [EASA] AD 2007-0238 was revised to exclude 
reference to Airbus SB A310-53-2124 Revision 01 and to require 
accomplishment of the task(s) as described in the original SB A310-
53-2124 instead, although retaining the reduced compliance times 
introduced by [EASA] AD 2007-0238 at original issue.
    EASA AD 2008-0212, superseding [EASA] AD 2007-0238R1, was 
published to refer to Airbus SB A310 53-2124 Revision 02, the 
corrected version that was used to meet the requirements of this 
[EASA] AD.
    Since [EASA] AD 2008-0212 was issued, new investigations in the 
frame of the Widespread Fatigue Damage campaign induced thresholds 
reduction, and Airbus issued SB A310-53-2124 Revision 03.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2008-0212, which is superseded, and requires 
accomplishment of modification(s) within reduced compliance time, as 
published in Airbus SB A310-53-2124 Revision 03.

    Required actions include a high frequency eddy current (HFEC) 
rotating probe inspection for cracking of certain fastener holes on 
certain frames, and related investigative and corrective actions if 
necessary; and modification of certain fastener holes. Related 
investigative actions include an additional HFEC rotating probe 
inspection for cracking of fastener holes and a check to determine the 
edge distance of certain holes. Corrective actions include ream out of 
cracks and repair.
    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-2017-
0695.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM and 
the FAA's response to that comment.

Request To Revise the Costs of Compliance

    FedEx stated that repairs would cost an additional $10,000 per 
airplane. The commenter noted that 66% of its past accomplishments 
required additional efforts to incorporate the modification with 
supplementary repair activities. The commenter suggested that the 
average cost of compliance would approach $30,000 per airplane. We 
infer that the commenter is requesting a revision to the costs of 
compliance in the NPRM. We agree with commenter's request to revise the 
costs of compliance in this final rule. We have revised the Costs of 
Compliance section in this final rule accordingly.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the change described previously, and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A310-53-2124, Revision 03, dated 
December 22, 2014. This service information describes procedures for a 
rotating probe inspection for cracking between frame (FR) 43 through FR 
46 on the center box, and the cold expansion (modification) of the most 
fatigue sensitive fastener 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.

Costs of Compliance

    We estimate that this AD affects 8 airplanes of U.S. registry.
    We estimate that it will take about 41 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $20,180 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S.

[[Page 11401]]

operators to be $189,320, or $23,665 per product.
    Although we have received no definitive data that will enable us to 
provide cost estimates for the on-condition actions (i.e., additional 
inspection and modification for certain airplanes) specified in this 
AD, we have determined that the total repair costs could be up to 
$10,000 per product. We have no way of determining the number of 
aircraft that might need these repairs.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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) 
2009-18-16, Amendment 39-16012 (74 FR 46342, September 9, 2009), and 
adding the following new AD:

2018-06-03 Airbus: Amendment 39-19223; Docket No. FAA-2017-0695; 
Product Identifier 2016-NM-173-AD.

(a) Effective Date

    This AD is effective April 19, 2018.

(b) Affected ADs

    This AD replaces AD 2009-18-16, Amendment 39-16012 (74 FR 46342, 
September 9, 2009) (``AD 2009-18-16'').

(c) Applicability

    This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324 and -325 airplanes; certificated in any category; 
all serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder indicating that the junctions of center box upper frame bases 
to the upper fuselage arches are subject to widespread fatigue 
damage and that the compliance threshold for the modification in AD 
2009-18-16 should be reduced. We are issuing this AD to prevent 
fatigue cracking of the frame foot run-outs, which could lead to 
rupture of the frame foot and cracking in adjacent frames and skin, 
and which could result in reduced structural integrity of the 
airplane.

(f) Compliance

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

(g) Inspections and Modification of Fastener Holes

    Except for airplanes modified before the effective date of this 
AD using the Accomplishment Instructions of Airbus Service Bulletin 
A310-53-2124: At the times specified in paragraph (g)(1) of this AD 
but no later than the times specified in paragraph (g)(2) of this 
AD, do a high frequency eddy current (HFEC) rotating probe 
inspection for cracking of fastener holes H1 through H29 on frames 
43 through 46, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A310-53-2124, Revision 03, 
dated December 22, 2014, except as required by paragraph (h) of this 
AD. If no cracking is found and the edge distance of the fastener 
hole is equal to or greater than the distance specified in the 
Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, 
Revision 03, dated December 22, 2014, before further flight, do the 
modification (cold expansion) of the affected fastener holes, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-53-2124, Revision 03, dated December 22, 2014. Do all 
applicable related investigative and corrective actions before 
further flight.
    (1) Inspect at the applicable time specified in table 1 to 
paragraph (g)(1) of this AD, or within 24 months after the effective 
date of this AD, whichever occurs later. To establish the average 
flight time (AFT), take the accumulated flight time (counted from 
the take-off up to the landing) and divide by the number of 
accumulated flight cycles. This gives the AFT per flight cycle. 
Although the thresholds for Model A310-304, -322, -324, and -325 
airplanes are optimized to airplane utilization, an operator can 
choose to use the thresholds for the other AFT.

[[Page 11402]]

[GRAPHIC] [TIFF OMITTED] TR15MR18.002

    (2) Inspect at the later of the times specified in paragraphs 
(g)(2)(i) and (g)(2)(ii) of this AD.
    (i) At the applicable time indicated in table 2 to paragraph 
(g)(2)(i) of this AD. Airbus Model A310-304, -322, -324, and -325 
airplanes with an AFT equal to or less than 3.16 flight hours are 
short range airplanes. Airbus Model A310-304, -322, -324, and -325 
airplanes with an AFT exceeding 3.16 flight hours are long range 
airplanes. For this paragraph, to establish the average flight time, 
take the accumulated flight time (counted from the take-off up to 
the landing) and divide by the number of accumulated flight cycles. 
This gives the AFT per flight cycle.

[[Page 11403]]

[GRAPHIC] [TIFF OMITTED] TR15MR18.003

    (ii) Within 500 flight cycles or 800 flight hours after October 
14, 2009 (the effective date of AD 2009-18-16), whichever occurs 
first.

(h) Service Information Exception

    Where Airbus Service Bulletin A310-53-2124, Revision 03, dated 
December 22, 2014, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (required for 
compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (l)(2) of this 
AD.

(i) Airplanes Modified per Revision 01 of the Service Information

    For airplanes modified before the effective date of this AD 
using Airbus Service Bulletin A310-53-2124, Revision 01, dated May 
3, 2007: Unless already accomplished, before further flight, do 
applicable corrective actions using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
the European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(j) Additional Inspection and Modification

    Except as provided by paragraphs (j)(1) and (j)(2) of this AD, 
as applicable: At the applicable thresholds specified in table 3 to 
the introductory text of paragraph (j) of this AD, contact the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA for additional inspection and 
modification instructions. Accomplish those instructions within the 
compliance times approved by the Manager, International Section, 
Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

[[Page 11404]]

[GRAPHIC] [TIFF OMITTED] TR15MR18.004

    (1) For Model A310-203, -204, -221, and -222 airplanes: No 
additional inspection is required if the inspection and modification 
specified in Airbus Service Bulletin A310-53-2124 was done after the 
accumulation of 29,500 flight cycles and 70,900 flight hours since 
the first flight of the airplane.
    (2) For Model A310-304, -322, -324, and -325 airplanes: No 
additional inspection is required if the inspection and modification 
specified in Airbus Service Bulletin A310-53-2124 was done after the 
accumulation of 22,600 flight cycles and 69,400 flight hours since 
the first flight of the airplane.

(k) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the Accomplishment Instructions of 
Airbus Service Bulletin A310-53-2124, dated April 4, 2005; or Airbus 
Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (m)(2) of this AD. Information 
may be emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (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 Section, Transport Standards 
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, 
the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as provided by 
paragraph (h) of this AD: 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 2016-0197, dated October 5, 2016, 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-2017-0695.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone: 
206-231-3225.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(4) of this AD.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A310-53-2124, Revision 03, dated 
December 22, 2014.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 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.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-05018 Filed 3-14-18; 8:45 am]
 BILLING CODE 4910-13-P