82 FR 43160 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 177 (September 14, 2017)

We are superseding Airworthiness Directive (AD) 2004-23-20, which applied to certain Airbus Model A300, A300 B4-600, and A300 B4- 600R series airplanes; and Model A300 F4-605R and A300 C4-605R Variant F airplanes. AD 2004-23-20 required, for certain airplanes, repetitive inspections for cracking around certain attachment holes, installation of new fasteners for certain airplanes, and follow-on corrective actions if necessary. AD 2004-23-20 also required modifying certain fuselage frames, which terminated certain repetitive inspections. This new AD reduces certain compliance times, expands the applicability, and requires an additional repair on certain modified airplanes. This AD was prompted by a report indicating that the material used to manufacture the upper frame feet was changed and negatively affected the fatigue life of the frame feet. We are issuing this AD to address the unsafe condition on these products.

[Federal Register Volume 82, Number 177 (Thursday, September 14, 2017)]
[Rules and Regulations]
[Pages 43160-43163]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-19303]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0451; Product Identifier 2013-NM-253-AD; Amendment 
39-19026; AD 2017-18-17]
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) 2004-23-20, 
which applied to certain Airbus Model A300, A300 B4-600, and A300 B4-
600R series airplanes; and Model A300 F4-605R and A300 C4-605R Variant 
F airplanes. AD 2004-23-20 required, for certain airplanes, repetitive 
inspections for cracking around certain attachment holes, installation 
of new fasteners for certain airplanes, and follow-on corrective 
actions if necessary. AD 2004-23-20 also required modifying certain 
fuselage frames, which terminated certain repetitive inspections. This 
new AD reduces certain compliance times, expands the applicability, and 
requires an additional repair on certain modified airplanes. This AD 
was prompted by a report indicating that the material used to 
manufacture the upper frame feet was changed and negatively affected 
the fatigue life of the frame feet. We are issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective October 19, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 19, 
2017.

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, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0451.

[[Page 43161]]

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-
0451; 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, 1601 Lind Avenue 
SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2004-23-20, Amendment 39-13875 (69 
FR 68779, November 26, 2004) (``AD 2004-23-20''). AD 2004-23-20 applied 
to certain Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R 
series airplanes; and Model A300 F4-605R and A300 C4-605R Variant F 
airplanes. The SNPRM published in the Federal Register on June 15, 2017 
(82 FR 27444) (``the SNPRM''). We preceded the SNPRM with a notice of 
proposed rulemaking (NPRM) that published in the Federal Register on 
February 1, 2016 (81 FR 5056) (``the NPRM''). The NPRM was prompted by 
a report indicating that the material used to manufacture the upper 
frame feet was changed and negatively affected the fatigue life of the 
frame feet. The NPRM proposed to reduce the compliance times for the 
initial inspection and the inspection intervals. The NPRM also proposed 
to expand the applicability and require an additional repair on certain 
airplanes that have been modified. The SNPRM proposed to reduce the 
compliance times, require an additional modification, and omit the 
requirement for the repetitive inspections. We are issuing this AD to 
prevent cracking of the center section of the fuselage, which could 
result in a ruptured frame foot and 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 
2016-0249, dated December 14, 2016; corrected January 10, 2017 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''); to correct an unsafe condition for all 
Airbus Model A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 
B4-622R, A300 F4-605R, A300 F4-622R, and A300 C4-605R Variant F 
airplanes. The MCAI states:

    During an inspection in accordance with Airworthiness Limitation 
Item (ALI) 53-15-54 on an A300-600 aeroplane, Frames (FR) 43, FR44, 
FR45 and FR46 were found cracked between stringer (STGR) 24 and 
STGR30 on the aeroplane right hand side. FR45 was also found cracked 
on the aeroplane left hand side.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the fuselage.
    To address this potential unsafe condition and improve the 
fatigue life of the upper frame feet fittings, Airbus issued Service 
Bulletin (SB) A300-53-6125 to provide instructions for expansion of 
the most sensitive fastener holes between FR41 and FR46. DGAC 
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France 
issued AD F-2004-002 (EASA approval 2003-2108) [which corresponds to 
FAA AD 2004-23-20] to require the structural modification defined in 
SB A300-53-6125 Revision 03 (Airbus modification 12168).
    [French] AD F-2004-002 was subsequently superseded by EASA AD 
2013-0295 to amend the inspection programme in this area as provided 
in SB A300-53-6122 (which is now obsolete and replaced by ALI task 
531558, published in the [Airworthiness Limitation Section] ALS Part 
2 Revision 01 dated 07 August 2015).
    Since EASA AD 2013-0295 was issued, a new investigation was 
conducted in the frame of the Widespread Fatigue Damage study. 
Airbus revised the thresholds for the accomplishment of the 
instructions defined in SB A300-53-6125 and issued SB A300-53-6178 
to provide modification instructions to improve the fatigue life of 
upper frame feet fittings on aeroplane[s] on which Airbus 
modification (mod) 12168 or Airbus SB A300-53-6125 was embodied.
    For the reason described above, this [EASA] AD retains some 
requirements of EASA AD 2013-0295, which is superseded, and requires 
modification of the upper frame feet fittings from FR41 to FR46 
[repetitive inspections are not retained].
    This [EASA] AD is republished to correct a typographical error 
in the compliance time * * *.

    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-
0451.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM or on the determination 
of the cost to the public.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-53-6125, Revision 04, dated 
March 17, 2015; and Service Bulletin A300-53-6178, dated March 17, 
2015. The service information describes procedures for the modification 
of certain upper frame feet fittings. These documents are distinct 
since they apply to airplanes in different configurations. 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 65 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:
    The actions that were required by AD 2004-23-20 and retained in 
this AD take about 90 work-hours per product, at an average labor rate 
of $85 per work-hour. Required parts cost about $4,000 per product. 
Based on these figures, the estimated cost of the actions that were 
required by AD 2004-23-20 is $11,650 per product.
    We also estimate that it will take up to 109 work-hours per product 
to comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost up to $6,070 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be up to $996,775, or up to $15,335 per product.
    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in this 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

[[Page 43162]]

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) 
2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), and 
adding the following new AD:

2017-18-17 Airbus: Amendment 39-19026; Docket No. FAA-2016-0451; 
Product Identifier 2013-NM-253-AD.

(a) Effective Date

    This AD is effective October 19, 2017.

(b) Affected ADs

    This AD replaces AD 2004-23-20, Amendment 39-13875 (69 FR 68779, 
November 26, 2004) (``AD 2004-23-20'').

(c) Applicability

    This AD applies to Airbus Model A300 B4-603, A300 B4-620, A300 
B4-622, A300 B4-605R, A300 B4-622R, A300 F4-605R, A300 F4-622R, and 
A300 C4-605R Variant F airplanes; certificated in any category; all 
manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by a report indicating that the material 
used to manufacture the upper frame feet was changed and negatively 
affected the fatigue life of the frame feet. We are issuing this AD 
to prevent cracking of the center section of the fuselage, which 
could result in a ruptured frame foot and reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Modification of the Upper Frame Feet Fittings

    (1) Except for airplanes identified in table 2 to paragraphs 
(g)(1) and (g)(2) of this AD: At the times specified in table 1 to 
paragraph (g)(1) of this AD, depending on the average flight time 
(AFT), as defined in paragraph (i) of this AD, modify the upper 
frame feet fittings, including doing all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6125, 
Revision 04, dated March 17, 2015 (``SB A300-53-6125, Revision 
04''). Do all applicable related investigative and corrective 
actions before further flight. Where Airbus SB A300-53-6125, 
Revision 04, 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.

  Table 1 to Paragraph (g)(1) of This AD--Modification SB A300-53-6125,
                               Revision 04
------------------------------------------------------------------------
                               Initial compliance time (flight cycles or
        Airplane usage            flight hours, whichever occurs first
                                          since first flight)
------------------------------------------------------------------------
AFT greater than 1.5.........  Within 10,200 flight cycles or 22,100
                                flight hours.
AFT equal to or less than 1.5  Within 11,000 flight cycles or 16,600
                                flight hours.
------------------------------------------------------------------------


Table 2 to Paragraphs (g)(1) and (g)(2) of This AD--Modification SB A300-
                                 53-6178
------------------------------------------------------------------------
    Airplane configuration              Initial compliance time
------------------------------------------------------------------------
Post-modification 12168......  Within 27,100 flight cycles or 47,300
                                flight hours since the airplane's first
                                flight, whichever occurs first.
Post-SB A300-53-6125.........  Within 27,100 flight cycles or 47,300
                                flight hours after embodiment of SB A300-
                                53-6125, whichever occurs first.
------------------------------------------------------------------------

    (2) For airplanes identified in table 2 to paragraphs (g)(1) and 
(g)(2) of this AD: At the applicable compliance time specified in 
table 2 to paragraphs (g)(1) and (g)(2) of this AD, modify the upper 
frame feet fittings, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6178, dated March 
17, 2015. Where Airbus Service Bulletin A300-53-6178, dated March 
17, 2015, specifies to contact Airbus for appropriate action, and 
specifies that action as ``RC'': Before further flight,

[[Page 43163]]

accomplish corrective actions in accordance with the procedures 
specified in paragraph (l)(2) of this AD.

(h) Additional Post-Modification Actions

    Prior to exceeding 24,100 total flight cycles or 42,000 total 
flight hours, whichever occurs first after doing the modification 
required by paragraph (g)(2) of this AD: Contact the Manager, 
International Section, Transport Standards Branch, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA); for instructions to do additional 
actions, and do those actions at the compliance times stated 
therein.

(i) Definition of AFT

    For the purpose of this AD, to establish the applicable AFT for 
the actions required by paragraph (g)(1) of this AD, divide the 
total accumulated flight hours counted from take-off to touch-down 
by the total accumulated flight cycles as of the effective date of 
this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the modification required by 
paragraph (g)(1) of this AD, if the modification was performed 
before the effective date of this AD using the service information 
specified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD.
    (1) Airbus Service Bulletin A300-53-6125, dated November 8, 
2000, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-53-6125, Revision 01, dated 
June 13, 2003, which was incorporated by reference in AD 2004-23-20.
    (3) Airbus Service Bulletin A300-53-6125, Revision 02, dated 
February 25, 2005, which is not incorporated by reference in this 
AD.
    (4) Airbus Service Bulletin A300-53-6125, Revision 03, dated 
September 13, 2011, which is not incorporated by reference in this 
AD.

(k) Exempt Airplanes

    For airplanes on which Airbus Modification 12168 has been 
embodied in production: The modification required by paragraph 
(g)(1) of this AD is not required by this AD.

(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 required by 
paragraphs (g)(1) and (g)(2) 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 Airworthiness Directive 2016-0249, dated December 14, 
2016; corrected January 10, 2017; 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-
2016-0451.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-
227-2125; fax 425- 227-1149.
    (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 A300-53-6125, Revision 04, dated 
March 17, 2015.
    (ii) Airbus Service Bulletin A300-53-6178, dated March 17, 2015.
    (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, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (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 August 29, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-19303 Filed 9-13-17; 8:45 am]
BILLING CODE 4910-13-P