Document ID: FAA-2015-0824-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2015-04-14T04:00Z

[Federal Register Volume 80, Number 71 (Tuesday, April 14, 2015)]
[Proposed Rules]
[Pages 19892-19895]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-08071]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0824; Directorate Identifier 2013-NM-191-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) 98-20-27, 
for all Airbus Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called Model A300-600 series airplanes). AD 98-20-27 currently requires 
repetitive inspections to detect fatigue cracking of the wing top skin 
at the front spar joint; and a follow-on eddy current inspection and 
repair, if necessary. Since we issued AD 98-20-27, we have received 
reports of cracking of the wing top skin in an area not required for 
inspection by AD 98-20-27. This proposed AD would reduce the inspection 
compliance time and intervals, and extend the inspection area of the 
wing top skin at the front spar joint. We are proposing this AD to 
detect and correct fatigue cracking of the wing top skin at the front 
spar joint, which could result in reduced structural integrity of the 
airplane.

DATES: We must receive comments on this proposed AD by May 29, 2015.

ADDRESSES: You may send comments 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 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 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-
0824; 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
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-2015-0824; 
Directorate Identifier 2013-NM-191-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 September 16, 1998, we issued AD 98-20-27, Amendment 39-10793 
(63 FR 50981, September 24, 1998). AD 98-20-27 requires actions 
intended to address an unsafe condition on all Airbus Model A300 B4-
600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes).
    Since we issued AD 98-20-27, Amendment 39-10793 (63 FR 50981, 
September 24, 1998): The European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Union, has 
issued EASA Airworthiness Directive 2013-0232R1, dated October 2, 2013 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition. The MCAI 
states:

    During full-scale fatigue testing conducted in the early 1990's, 
cracks were found on the top skin of the wing between Ribs 1 and 7, 
starting at the front spar fastener holes.
    This condition, if not detected and corrected, could adversely 
affect the structural integrity of the wing.
    Consequently, Airbus issued Service Bulletin (SB) A300-57-6045 
and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued AD 97-374-238 [http://ad.easa.europa.eu/blob/19973740tb_superseded.pdf/AD_F-1997-374-238_2] for A300-600 
aeroplanes and AD 1999-008-020 [http://ad.easa.europa.eu/blob/19980080tb_superseded.pdf/AD_F-1999-008-020_2] for A300-600ST 
aeroplanes to require repetitive detailed inspections of the wing 
top skin and, in case of findings, an Eddy Current (EC) inspection, 
and, depending on the size of the cracks, repair.
    After those [DGAC] ADs were issued, further cracks to the wing 
top skin were reported by operators, within an area not covered by 
the existing [DGAC] ADs. To address this potential unsafe condition, 
Airbus revised SB A300-57-6045 to extend the area to be inspected.
    In addition, a fleet survey and updated Fatigue and Damage 
Tolerance analyses were performed in order to substantiate the 
second A300-600 Extended Service Goal (ESG2) exercise. The results 
of these analyses have determined that the inspection thresholds and 
intervals must be reduced to allow timely detection of these cracks 
and the accomplishment of applicable corrective action(s).
    As the ESG2 exercise is only applicable to A300-600 aeroplanes, 
A300-600ST aeroplanes are now addressed through new Airbus SB A300-
57-9026.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 97-374-238(B) [http://ad.easa.europa.eu/blob/19973740tb_superseded.pdf/AD_F-1997-374-238_2] [which corresponds to FAA AD 98-20-27, Amendment 39-10793 (63 
FR 50981, September 24, 1998)] and [DGAC] AD 1999-008-020(B) [http://ad.easa.europa.eu/blob/19980080tb_superseded.pdf/AD_F-1999-008-020_2], which are superseded, but requires

[[Page 19893]]

those actions, for A300-600 aeroplanes only, within reduced 
thresholds and intervals.

* * * * *
    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-
0824.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6045, Revision 10, dated 
November 13, 2013. The service information describes inspection 
procedures for fatigue cracking of the wing top skin at the front spar 
joint between ribs 1 and 7. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI. This service information is reasonably available; see 
ADDRESSES for ways to access this service information.

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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Unlike the procedures described in the MCAI and Airbus Service 
Bulletin A300-57-6045, Revision 10, dated November 13, 2013, this 
proposed AD would not permit further flight if cracks are detected in 
the wing top skin at the front spar joint. We have determined that, 
because of the safety implications and consequences associated with 
that cracking, any cracked wing top skin at the front spar joint must 
be repaired before further flight. This difference has been coordinated 
with the EASA.

Costs of Compliance

    We estimate that this proposed AD affects 130 airplanes of U.S. 
registry.
    The actions that are required by AD 98-20-27, Amendment 39-10793 
(63 FR 50981, September 24, 1998), and retained in this proposed AD 
take about 2 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 98-20-27 is $170 per product.
    We also estimate that it would take about 2 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $22,100, or $170 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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 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) 
98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-0824; Directorate Identifier 2013-NM-
191-AD.

(a) Comments Due Date

    We must receive comments by May 29, 2015.

(b) Affected ADs

    This AD replaces AD 98-20-27, Amendment 39-10793 (63 FR 50981, 
September 24, 1998).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of cracking of wing top skin in 
an area not required for inspection by AD 98-20-27, Amendment 39-
10793 (63 FR 50981, September 24, 1998). We are issuing this AD to 
detect and correct fatigue cracking of the wing top skin at the 
front spar joint, 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) Retained Repetitive Inspections, With Revised Service Information

    This paragraph restates the requirements of paragraph (a) of AD 
98-20-27, Amendment

[[Page 19894]]

39-10793 (63 FR 50981, September 24, 1998), with revised service 
information. Prior to the accumulation of 22,000 total flight 
cycles, or within 2,000 flight cycles after October 29, 1998 (the 
effective date of AD 98-20-27), whichever occurs later: Perform a 
detailed visual inspection to detect fatigue cracking of the wing 
top skin at the front spar joint, in accordance with Airbus Service 
Bulletin A300-57-6045, Revision 1, dated August 3, 1994, including 
Appendix 1, Revision 1, dated August 3, 1994; Airbus Service 
Bulletin A300-57-6045, Revision 02, dated April 21, 1998, including 
Appendix 1, Revision 02, dated April 21, 1998; or Airbus Service 
Bulletin A300-57-6045, Revision 10, dated November 13, 2013. Repeat 
the detailed visual inspection thereafter at intervals not to exceed 
8,000 flight cycles.

(h) Retained Inspection and Repair, With Revised Service Information

    This paragraph restates the requirements of paragraph (b) of AD 
98-20-27, Amendment 39-10793 (63 FR 50981, September 24, 1998), with 
revised service information. If any cracking is suspected or 
detected during any inspection required by paragraph (g) of this AD: 
Prior to further flight, perform an eddy current inspection to 
confirm the findings of the visual inspection, in accordance with 
Airbus Service Bulletin A300-57-6045, Revision 01, dated August 3, 
1994, including Appendix 1, Revision 01, dated August 3, 1994; 
Airbus Service Bulletin A300-57-6045, Revision 02, dated April 21, 
1998, including Appendix 1, Revision 02, dated April 21, 1998; or 
Airbus Service Bulletin A300-57-6045, Revision 10, dated November 
13, 2013. If any cracking is detected during any eddy current 
inspection, prior to further flight, repair using a method approved 
by the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate; or the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (or its delegated agent).

(i) New Requirement of This AD: Initial Inspection

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD: Do a detailed inspection of the wing top skin between 
ribs one and seven for cracking, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6045, 
Revision 10, dated November 13, 2013. Accomplishment of the initial 
inspection required by this paragraph terminates the requirements of 
paragraph (g) of this AD.
    (1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, 
Model A300 B4-605R and B4-622R airplanes, and Model A300 C4-605R 
Variant F airplanes: At the later of the times specified in 
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
    (i) Before the accumulation of 17,100 total flight cycles or 
38,400 total flight hours, whichever occurs first.
    (ii) Within 1,000 flight cycles or 2,200 flight hours, whichever 
occurs first after the effective date of this AD.
    (2) For Model A300 F4-605R and F4-622R airplanes: At the later 
of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of 
this AD.
    (i) Before the accumulation of 22,000 total flight cycles or 
49,500 total flight hours, whichever occurs first.
    (ii) Within 1,300 flight cycles or 2,800 flight hours, whichever 
occurs first after the effective date of this AD.

(j) New Requirement of This AD: Repetitive Inspections

    Repeat the inspection required by paragraph (i) of this AD 
thereafter at the applicable time and intervals specified in 
paragraphs (j)(1) and (j)(2) of this AD.
    (1) For Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, 
Model A300 B4-605R and B4-622R airplanes, and Model A300 C4-605R 
Variant F airplanes: At the applicable time specified in paragraph 
(j)(1)(i) or (j)(1)(ii) of this AD.
    (i) For airplanes that have an average flight time (AFT) that is 
equal to or more than one and one-half hours: At intervals not to 
exceed 5,100 flight cycles or 11,000 flight hours, whichever occurs 
first.
    (ii) For airplanes that have an AFT that is less than one and 
one-half hours: At intervals not to exceed 5,500 flight cycles or 
8,300 flight hours, whichever occurs first.
    (2) For Model A300 F4-605R and F4-622R airplanes: At the 
applicable time specified in paragraph (j)(2)(i) or (j)(2)(ii) of 
this AD.
    (i) For airplanes that have an AFT that is equal to or more than 
one and one-half hours: At intervals not to exceed 6,500 flight 
cycles or 14,100 flight hours, whichever occurs first.
    (ii) For airplanes that have an AFT that is less than one and 
one-half hours: At intervals not to exceed 7,000 flight cycles or 
10,600 flight hours, whichever occurs first.

(k) New Requirement of This AD: Repair of Cracking

    (1) If any crack in the top skin in the area forward of the 
front spar attachment is found during any inspection required by 
paragraph (i) of this AD: Before further flight, repair using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
    (2) If any crack or sign of a crack is found in the top skin at 
or aft of the spar attachment during any inspection required by 
paragraph (i) of this AD: Before further flight, do an eddy current 
inspection of the cracks or of the signs of cracking to confirm the 
findings of the detailed inspection, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6045, 
Revision 10, dated November 13, 2013. If there are any cracks at or 
aft of the spar attachment, before further flight, repair using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; EASA; or Airbus's EASA DOA.

(l) No Terminating Action

    Accomplishment of any repair required by paragraph (k) this AD 
does not constitute terminating action for the repetitive 
inspections required by paragraph (j) of this AD.

(m) No Reporting Required

    Although Airbus Service Bulletin A300-57-6045, Revision 10, 
dated November 13, 2013, specifies to submit certain information to 
the manufacturer, this AD does not include that requirement.

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (i), (j) and (k) of this AD, if those actions were 
performed before the effective date of this AD using the Airbus 
service bulletins specified in paragraphs (n)(1) through (n)(10) of 
this AD, which are not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A300-57-6045, dated March 18, 1993.
    (2) Airbus Service Bulletin A300-57-6045, Revision 01, dated 
August 3, 1994.
    (3) Airbus Service Bulletin A300-57-6045, Revision 02, dated 
April 21, 1998.
    (4) Airbus Service Bulletin A300-57-6045, Revision 03, dated 
October 25, 1999.
    (5) Airbus Service Bulletin A300-57-6045, Revision 04, dated 
January 13, 2002.
    (6) Airbus Service Bulletin A300-57-6045, Revision 05, dated 
June 13, 2003.
    (7) Airbus Service Bulletin A300-57-6045, Revision 06, dated 
January 13, 2005.
    (8) Airbus Service Bulletin A300-57-6045, Revision 07, dated 
August 14, 2008.
    (9) Airbus Service Bulletin A300-57-6045, Revision 08, dated 
June 6, 2011.
    (10) Airbus Service Bulletin A300-57-6045, Revision 09, dated 
May 21, 2013.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International 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 Branch, send it 
to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (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. The AMOC approval letter must specifically 
reference this AD.
    (ii) AMOCs approved previously for AD 98-20-27, Amendment 39-
10793 (63 FR 50981, September 24, 1998), are approved as AMOCs for 
the corresponding provisions of this AD.
    (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 Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

[[Page 19895]]

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0232R1, dated October 2, 
2013, 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-2015-0824.
    (2) 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 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 March 27, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-08071 Filed 4-13-15; 8:45 am]
 BILLING CODE 4910-13-P