[Federal Register Volume 84, Number 158 (Thursday, August 15, 2019)]
[Unknown Section]
[Pages 41623-41626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-17503]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0319; Product Identifier 2019-NM-005-AD; Amendment 
39-19701; AD 2019-15-08]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2002-07-
05, which applied to all Airbus Model A300 B2, A300 B4, A300 B4-600, 
and A300 B4-600R series airplanes, and Model A300 F4-605R airplanes. AD 
2002-07-05 required repetitive inspections for cracking of certain 
fittings, corrective action if necessary, and, for certain airplanes, a 
modification. This AD requires repetitive inspections for cracking of 
certain fittings, corrective actions if necessary, and, for certain 
airplanes, a modification; as specified in a European Union Aviation 
Safety Agency (EASA) AD, which is incorporated by reference. This AD 
was prompted by a determination that, for certain airplanes, the 
existing inspection compliance times were not sufficient to address the 
unsafe condition and needed to be reduced. The FAA is issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective September 19, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
19, 2019.

ADDRESSES: For the material incorporated by reference (IBR) in this AD, 
contact the EASA, at Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 89990 1000; email [email protected]; internet 
www.easa.europa.eu. You may find this IBR material on the EASA website 
at https://ad.easa.europa.eu. You may view this referenced 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. It is also available on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2019-0319.

[[Page 41624]]

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-2019-
0319; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations is 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 and fax 206-231-3225.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2002-07-05, Amendment 39-12699 (67 FR 
16983, April 9, 2002; corrected April 23, 2002 (67 FR 19810)) (``AD 
2002-07-05''). AD 2002-07-05 applied to all Airbus Model A300 B2, A300 
B4, A300 B4-600, and A300 B4-600R series airplanes, and Model A300 F4-
605R airplanes. The NPRM published in the Federal Register on May 9, 
2019 (84 FR 20300). The NPRM was prompted by reports of cracked frame 
(FR) 40 aft fittings at stringer 33 on the left and right sides of the 
fuselage, and a determination that the existing inspection compliance 
times were not sufficient to address the unsafe condition and needed to 
be reduced. The NPRM proposed to require repetitive inspections for 
cracking of certain fittings, corrective actions if necessary, and, for 
certain airplanes, a modification. The FAA is issuing this AD to 
address propagation of cracks on the FR40 aft fittings due to local 
stress concentrations at the upper flange runout of FR40, which could 
result in reduced structural integrity of the airplane.
    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2019-0011R1, dated February 22, 2019 
(``EASA AD 2019-0011R1'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Airbus SAS Model A300 series airplanes; Model A300 
B4-600 series airplanes; Model A300 B4-600R series airplanes; and Model 
A300 C4-605R Variant F airplanes; and certain Model A300 F4-605R 
airplanes. The MCAI states:

    After embodiment of Airbus SB [service bulletin] A300-53-0161, 
cracks were reported on three aeroplanes. Investigations highlighted 
that these cracks were caused by a local stress concentration at 
FR40 upper flange run-out, where the profile of the FR40 changes at 
the centre wing box connection.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    Subsequently to this finding, Airbus established a High 
Frequency Eddy Current (HFEC) inspection program for A300 aeroplanes 
implemented in service through Airbus SB A300-53-0296. In the same 
time, Airbus launched mod. 10430 in production line associated to SB 
A300-53-6048 for the retrofit campaign for A300-600. The same HFEC 
inspection program was defined for A300-600 aeroplanes and included 
in SB A300-53-6048 instructions.
    [Direction Generale de l'Aviation Civile] DGAC France AD F-1998-
481-270 [which corresponds to FAA AD 2002-07-05] was published to 
mandate the embodiment of these two SBs.
    DGAC France AD F-2000-038-032 was also published later to 
mandate Airbus SB A300-53-9017 applicable to A300-600ST aeroplanes.
    Since DGAC France AD F-1998-481-270 and F-2000-038-032 were 
issued, material data used in the frame of fatigue and damage 
tolerance analysis has been changed. It was determined that the 
existing threshold and interval values must be reduced for A300-600 
and A300-600ST fleet. Consequently, Airbus revised SB A300-53-6048 
to Revision 05 and SB A300-53-9017 to Revision 02 to take into 
account the new thresholds and intervals.
    For the reasons described above, this [EASA] AD retains the 
requirement of DGAC France AD F-1998-481-270R2 and F-2000-038-032R1, 
which are superseded, and introduces new thresholds and intervals 
for A300-600 and A300-600ST aeroplanes.
    This [EASA] AD is revised to correct a typo in the 
Applicability, introduces Tables 1a and 1b, replacing original Table 
1, to clarify inspection compliance times, and removes Note 1. This 
revised [EASA] AD also grants credit for actions accomplished using 
previous revisions of the applicable SB.

The MCAI added Model A300 C4-605R Variant F airplanes to its 
applicability because those airplanes are affected by the identified 
unsafe condition. Therefore, this AD also added Model A300 C4-605R 
Variant F airplanes to the applicability. Those airplanes were not on 
the U.S. type certificate data sheet at the time AD 2002-07-05 was 
issued. 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-2019-0319.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
except for minor editorial changes. The FAA has determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2019-0011R1 describes procedures for modifying the profile 
of the FR40 aft fittings for certain airplanes, repetitive HFEC 
inspections for cracking of certain fittings, corrective actions for 
any cracking found, and reporting inspections findings.
    This material 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

    The FAA estimates that this AD affects 66 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                                          Estimated Costs for Required Actions*
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                Action                          Labor cost           Parts cost             Cost per product                Cost on U.S.  operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Retained actions from AD 2002-07-05...  Up to 102 work-hours x               $874  Up to $9,544......................  Up to $629,904.
                                         $85 per hour = $8,670.

[[Page 41625]]

 
New actions...........................  Up to 37 work[dash]hours            2,550  Up to $5,695......................  Up to $375,870.
                                         x $85 per hour = $3,145.
--------------------------------------------------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    The FAA estimates that it would take about 1 work-hour per product 
to comply with the reporting requirement in this AD. The average labor 
rate is $85 per hour. Based on these figures, the FAA estimates the 
cost of reporting the inspection results on U.S. operators to be 
$5,610, or $85 per product.
    The FAA has received no definitive data that would enable us to 
provide cost estimates for the on-condition action specified in this 
AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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.
    The FAA is 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 and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    The FAA 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) Will not affect intrastate aviation in Alaska, and
    (3) 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) 
2002-07-05, Amendment 39-12699 (67 FR 16983, April 9, 2002; corrected 
April 23, 2002 (67 FR 19810)), and adding the following new AD:

2019-15-08 Airbus SAS: Amendment 39-19701; Docket No. FAA-2019-0319; 
Product Identifier 2019-NM-005-AD.

(a) Effective Date

    This AD is effective September 19, 2019.

(b) Affected ADs

    This AD replaces 2002-07-05, Amendment 39-12699 (67 FR 16983, 
April 9, 2002; corrected April 23, 2002 (67 FR 19810)) (``AD 2002-
07-05'').

(c) Applicability

    This AD applies to Airbus SAS Model airplanes specified in 
paragraphs (c)(1) through (c)(5) of this AD, certificated in any 
category, as identified in European Union Aviation Safety Agency 
(EASA) AD 2019-0011R1, dated February 22, 2019 (``EASA AD 2019-
0011R1'').
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 C4-605R Variant F airplanes.
    (5) Model A300 F4-605R airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracked frame (FR) 40 aft 
fittings at stringer 33 on the left and right sides of the fuselage, 
and a determination that the existing inspection compliance times 
were not sufficient to address the unsafe condition and needed to be 
reduced. We are issuing this AD to address propagation of cracks on 
the FR40 aft fittings due to local stress concentrations at the 
upper flange runout of FR40, 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) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and

[[Page 41626]]

compliance times specified in, and in accordance with, EASA AD 2019-
0011R1.

(h) Exceptions to EASA AD 2019-0011R1

    (1) For purposes of determining compliance with the requirements 
of this AD: Where EASA AD 2019-0011R1 refers to its effective date, 
or February 6, 2019 (the effective date of EASA AD 2019-0011, dated 
January 23, 2019), this AD requires using the effective date of this 
AD.
    (2) The ``Remarks'' section of EASA AD 2019-0011R1 does not 
apply to this AD.
    (3) Paragraphs (7) and (8) of EASA AD 2018-0011R1 specify to 
report inspection results to Airbus within a certain compliance 
time. For this AD, report inspection results at the applicable time 
specified in paragraph (h)(3)(i) or (h)(3)(ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(i) 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 (j) of this AD. Information may 
be emailed to: [email protected].
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (ii) AMOCs approved previously for AD 2002-07-05 are approved as 
AMOCs for the corresponding provisions of EASA AD 2019-0011R1 that 
are required by paragraph (g) of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): For any service information 
referenced in EASA AD 2019-0011R1 that contains RC procedures and 
tests: Except as required by paragraph (i)(2) of this AD, RC 
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.
    (4) Paperwork Reduction Act Burden Statement: A federal agency 
may not conduct or sponsor, and a person is not required to respond 
to, nor shall a person be subject to a penalty for failure to comply 
with a collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 1 
hour per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW, Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(j) Related Information

    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 
and fax 206-231-3225.

(k) 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) European Union Aviation Safety Agency (EASA) AD 2019-0011R1, 
dated February 22, 2019.
    (ii) [Reserved]
    (3) For EASA AD 2019-0011R1, contact the EASA, at Konrad-
Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 
6017; email [email protected]; internet www.easa.europa.eu. You may 
find this EASA AD on the EASA website at https://ad.easa.europa.eu.
    (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 Des Moines, Washington, on July 30, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-17503 Filed 8-14-19; 8:45 am]
 BILLING CODE 4910-13-P


