Document ID: FAA-2015-4817-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-04-11T04:00Z

[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)]
[Rules and Regulations]
[Pages 21255-21258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07570]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4817; Directorate Identifier 2014-NM-115-AD; 
Amendment 39-18465; AD 2016-07-20]
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) 95-18-08 for 
all Airbus Model A300-600 series airplanes. AD 95-18-08 required 
repetitive inspections to detect cracks in the bottom skin of the wing 
in the area of the cut-out for the pylon rear attachment fitting, and 
repair if necessary. This new AD, for certain

[[Page 21256]]

airplanes, reduces the compliance times for the inspections. This AD 
was prompted by a report that updated fatigue and damage tolerance 
analyses and a fleet survey found that certain inspection thresholds 
and intervals must be reduced to allow more timely findings of 
cracking. We are issuing this AD to detect and correct fatigue-related 
cracking in the bottom skin of the wing in the area of the cut-out for 
the pylon rear attachment fitting, which could result in reduced 
structural integrity of the wing.

DATES: This AD becomes effective May 16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 16, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
October 16, 1995 (60 FR 47677, September 14, 1995).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-4817; or in person at the 
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.
    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 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4817.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 95-18-08, Amendment 39-9355 (60 FR 47677, 
September 14, 1995) (``AD 95-18-08''). AD 95-18-08 applied to all 
Airbus Model A300-600 series airplanes (which includes Airbus Model 
A300 C4-605R Variant F airplanes), Model A300 B4-622 airplanes, and 
Model A300 F4-622R airplanes that were added to the U.S. Type 
Certificate Data Sheet since issuance of AD 95-18-08. The NPRM 
published in the Federal Register on November 19, 2015 (80 FR 72395) 
(``the NPRM'' or ``the proposed AD''). The NPRM was prompted by a 
report that updated fatigue and damage tolerance analyses and a fleet 
survey found that certain inspection thresholds and intervals must be 
reduced to allow more timely findings of cracking. The NPRM proposed to 
continue to require repetitive inspections to detect cracks in the 
bottom skin of the wing in the area of the cut-out for the pylon rear 
attachment fitting, and repair if necessary. The NPRM also proposed, 
for certain airplanes, reduce the compliance times for the inspections. 
We are issuing this AD to detect and correct such fatigue-related 
cracking in the bottom skin of the wing in the area of the cut-out for 
the pylon rear attachment fitting, which could result in reduced 
structural integrity of the wing.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0119, dated May 13, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct 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). The MCAI states:

    Full-scale fatigue tests carried out on the A300-600 test 
specimen by Airbus revealed crack initiation in the bottom skin 
adjacent to the aft pylon attachment fitting.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 94-
069-158(B) (http://ad.easa.europa.eu/blob/1994069158tb_superseded.pdf/AD_F-1994-069-158_2) [which corresponds 
to FAA AD 95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 
1995)] to require repetitive detailed visual inspections (DVI) of 
the wing bottom skin in the area of the cut-out for the pylon rear 
attachment fitting on Left Hand (LH) and Right Hand (RH) wings [to 
detect cracks, and repair if necessary].
    Since that [DGAC] AD was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analyses have been performed in order 
to substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. As a result, it was revealed that the inspection threshold 
and interval must be reduced to allow timely detection of cracks and 
the accomplishment of an applicable corrective action. Prompted by 
these findings, Airbus issued Revision 07 of Service Bulletin (SB) 
A300-57-6028.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 94-069-158(B), which is superseded, 
but reduces the inspection thresholds and intervals [e.g., 
compliance times].

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-4817-0002.

Comment

    The following presents the comment received on the NPRM and the 
FAA's response to the comment.

Statement on Fleet Activity

    FedEx Express (FedEx) stated that the NPRM will affect 71 Model 
A300 airplanes in its fleet. FedEx stated that 42 of its Model A300-F4 
airplanes have not reached the inspection threshold, and it is 
currently accomplishing repetitive actions on 15 of its 29 Model A300-
B4 airplanes. FedEx stated that it will adjust its inspection actions 
to comply with the actions specified in the NPRM.
    We acknowledge FedEx's comment. No change to this AD is necessary.

Conclusion

    We reviewed the available data, including the comment received, 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 
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

    We reviewed Airbus Service Bulletin A300-57-6028, Revision 07, 
dated June 6, 2011. The service information describes procedures for 
inspections to detect cracks in the bottom skin of the wing in the area 
of the cut-out for the pylon rear attachment fitting, and repair. 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.

[[Page 21257]]

Costs of Compliance

    We estimate that this AD affects 124 airplanes of U.S. registry.
    The actions required by AD 95-18-08, and retained in this AD take 
about 6 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 were required by AD 95-18-08 is $510 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 15 work-hours and require parts costing $10,000, for a cost 
of $11,275 per product. We have no way of determining the number of 
aircraft that might need these actions.
    The new requirements of this AD add no additional economic burden.

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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-4817; 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 street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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) 
95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995), and 
adding the following new AD:

2016-07-20 Airbus: Amendment 39-18465. Docket No. FAA-2015-4817; 
Directorate Identifier 2014-NM-115-AD.

(a) Effective Date

    This AD becomes effective May 16, 2016.

(b) Affected ADs

    This AD replaces AD 95-18-08, Amendment 39-9355 (60 FR 47677, 
September 14, 1995) (``AD 95-18-08'').

(c) Applicability

    This AD applies to the 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 a report that updated fatigue and damage 
tolerance analyses and a fleet survey found that certain inspection 
thresholds and intervals must be reduced to allow more timely 
findings of cracking. We are issuing this AD to detect and correct 
such fatigue-related cracking in the bottom skin of the wing in the 
area of the cut-out for the pylon rear attachment fitting, which 
could result in reduced structural integrity of the wing.

(f) Compliance

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

(g) Retained Inspection and Corrective Action with Additional Repair 
Information

    This paragraph restates the requirements of paragraph (a) of AD 
95-18-08, with additional repair contact information. Prior to the 
accumulation of 24,000 total flight cycles since date of manufacture 
of the airplane, or within 750 flight cycles after October 16, 1995 
(the effective date of AD 95-18-08), whichever occurs later, perform 
a detailed visual inspection to detect cracks in the bottom skin of 
the wing in the area of the cut-out for the pylon rear attachment 
fitting, in accordance with Airbus Service Bulletin A300-57-6028, 
Revision 3, dated September 13, 1994. Repeat the inspection 
thereafter at intervals not to exceed 9,000 flight cycles. If any 
crack is detected, prior to further flight, repair the wing bottom 
skin in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate, or the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). 
Accomplishing any inspection required by paragraph (h) of this AD 
terminates the inspections required by this paragraph.

(h) New Requirement of This AD: Revised Inspection Thresholds and 
Intervals

    Within the applicable compliance times required in paragraphs 
(h)(1) and (h)(2) of this AD, do a detailed visual inspection of the 
wing bottom skin in the area of the cut-out for the pylon rear 
attachment fitting on left-hand and right-hand wings, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-57-6028, Revision 07, dated June 6, 2011. Repeat the 
inspections thereafter at the applicable intervals required in 
paragraphs (h)(3) and (h)(4) of this AD. Accomplishing any 
inspection required by this paragraph terminates the inspections 
required by paragraph (g) of this AD.
    (1) For ``normal range operations'' airplanes having an average 
flight time of 1.5 flight hours or more: Do the inspection at the 
applicable time required in paragraphs (h)(1)(i) and (h)(1)(ii) of 
this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Do the 
inspection at the later of the times specified in paragraphs 
(h)(1)(i)(A) and (h)(1)(i)(B) of this AD.

[[Page 21258]]

    (A) Within 24,000 flight cycles or 51,800 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 2,000 flight cycles or 4,300 flight hours after the 
effective date of this AD, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Do the inspection at the later of the times 
specified in paragraphs (h)(1)(ii)(A) and (h)(1)(ii)(B) of this AD.
    (A) Within 19,100 flight cycles or 41,200 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 1,500 flight cycles or 3,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For ``short range operations'' airplanes having an average 
flight time of less than 1.5 flight hours: Do the inspection at the 
applicable time required in paragraphs (h)(2)(i) and (h)(2)(ii) of 
this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Do the 
inspection at the later of the times specified in paragraphs 
(h)(2)(i)(A) and (h)(2)(i)(B) of this AD.
    (A) Within 25,900 flight cycles or 38,800 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 2,100 flight cycles or 3,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Do the inspection at the later of the times 
specified in paragraphs (h)(2)(ii)(A) and (h)(2)(ii)(B) of this AD.
    (A) Within 20,600 flight cycles or 30,900 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 1,600 flight cycles or 2,400 flight hours after the 
effective date of this AD, whichever occurs first.
    (3) For ``normal range operations'' airplanes having an average 
flight time of 1.5 flight hours or more: Repeat the inspection at 
the applicable time required in paragraphs (h)(3)(i) and (h)(3)(ii) 
of this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Repeat the 
inspection thereafter at intervals not to exceed 9,000 flight cycles 
or 19,400 flight hours, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Repeat the inspection thereafter at intervals 
not to exceed 7,100 flight cycles or 15,300 flight hours, whichever 
occurs first.
    (4) For ``short range operations'' airplanes having an average 
flight time of less than 1.5 flight hours: Repeat the inspection at 
the applicable time required in paragraphs (h)(4)(i) and (h)(4)(ii) 
of this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Repeat the 
inspection thereafter at intervals not to exceed 9,700 flight cycles 
or 14,500 flight hours, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Repeat the inspection thereafter at intervals 
not to exceed 7,600 flight cycles or 11,500 flight hours, whichever 
occurs first.

(i) Definition of Average Flight Time for Paragraph (h) of This AD

    For the purpose of paragraph (h) of this AD, the Average Flight 
Time must be established as follows:
    (1) For the initial inspection, the average flight time is the 
total accumulated flight hours, counted from take-off to touch-down, 
divided by the total accumulated flight cycles at the effective date 
of this AD.
    (2) For the first repeated inspection interval, the average 
flight time is the total accumulated flight hours divided by the 
total accumulated flight cycles at the time of the inspection 
threshold.
    (3) For all inspection intervals onwards, the average flight 
time is the flight hours divided by the flight cycles accumulated 
between the last two inspections.

(j) New Requirement of This AD: Corrective Action for Any Cracking 
Found

    If any crack is found during any inspection required by 
paragraph (h) 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. 
Accomplishing a repair does not constitute terminating action for 
the repetitive inspections required by paragraph (h) of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for inspections required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using any of the service information 
identified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD, 
which are not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A300-57-6028, Revision 04, dated 
October 25, 1999.
    (2) Airbus Service Bulletin A300-57-6028, Revision 05, dated 
January 11, 2002.
    (3) Airbus Service Bulletin A300-57-6028, Revision 06, dated May 
17, 2006.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: 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 95-18-08, are approved as 
AMOCs for the corresponding provisions of paragraph (g) of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2014-
0119, dated May 13, 2014, 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-2015-4817.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(5) and (n)(6) 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.
    (3) The following service information was approved for IBR on 
May 16, 2016.
    (i) Airbus Service Bulletin A300-57-6028, Revision 07, dated 
June 6, 2011.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
October 16, 1995 (60 FR 47677, September 14, 1995).
    (i) Airbus Service Bulletin A300-57-6028, Revision 3, dated 
September 13, 1994. Pages 1 through 6 of this service bulletin 
indicate Revision 3 and are dated September 13, 1994; pages 7 
through 9 indicate Revision 2 and are dated February 22, 1994.
    (ii) Reserved.
    (5) 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.
    (6) 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.
    (7) 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 24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07570 Filed 4-8-16; 8:45 am]
 BILLING CODE 4910-13-P