Document ID: FAA-2015-4813-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-06-10T04:00Z

[Federal Register Volume 81, Number 112 (Friday, June 10, 2016)]
[Rules and Regulations]
[Pages 37488-37492]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-12324]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4813; Directorate Identifier 2013-NM-161-AD; 
Amendment 39-18532; AD 2016-11-05]
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) 99-16-01 for 
certain 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 99-16-01 required 
repetitive inspections of certain bolt holes where parts of the main 
landing gear (MLG) are attached to the wing rear spar, and repair if 
necessary. Since we issued AD 99-16-01, we have determined that the 
risk of cracking in the wing rear spar is higher than initially 
determined. This new AD adds airplanes to the applicability, reduces 
the compliance times and repetitive intervals for the inspections, and 
changes the inspection procedures. This AD was prompted by a 
determination that the risk of cracking in the wing rear spar is higher 
than initially determined. We are issuing this AD to detect and correct 
cracking of the rear spar of the wing, which could result in reduced 
structural integrity of the airplane.

DATES: This AD becomes effective July 15, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 15, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 9, 1995 (60 FR 52618, October 10, 1995).

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 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-
4813.

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-
4813; 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 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 99-16-01, Amendment 39-11236 (64 FR 40743, July 
28, 1999) (``AD 99-16-01''). AD 99-16-01 superseded AD 95-20-02, 
Amendment 39-9380 (60 FR 52618, October 10, 1995). AD 99-16-01 applied 
to certain 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 NPRM published in the 
Federal Register on November 17, 2015 (80 FR 71751) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0180, dated August 9, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain 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:

    During full-scale fatigue testing, cracks were found on the rear 
spar from certain bolt holes at the attachment of the Main Landing 
gear (MLG) forward pick-up fitting and the MLG Rib 5 aft.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the aeroplane.
    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued * * * [an AD] (later revised) to require High 
Frequency Eddy Current (HFEC) or Ultrasonic (U/S) inspections of 
certain fastener holes where the MLG forward pick-up fitting and MLG 
Rib 5 aft are attached to the rear spar.
    Since DGAC France * * * [issued a revised AD, which corresponded 
to FAA AD 99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), 
which superseded FAA AD 95-20-02, Amendment 39-9380 (60 FR 52618, 
October 10, 1995)] * * *, 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. The results of these analyses have shown that the 
threshold and interval must be reduced to allow timely detection of 
these cracks and accomplishment of an applicable corrective action.
    For the reasons described above, this [EASA] AD retains the 
requirements of [the revised DGAC France AD], which is superseded, 
but reduces the related compliance times.

The new, reduced threshold for the initial inspection ranges between 
8,900

[[Page 37489]]

total flight cycles/20,000 total flight hours, and 34,600 total flight 
cycles/77,800 total flight hours, depending on the modification. The 
grace periods (750 or 1,500 landings) for airplanes that have exceeded 
the specified thresholds are unchanged from those provided in AD 99-16-
01. The new, reduced intervals for the repetitive inspections range 
between 4,000 flight cycles/9,000 flight hours (whichever occurs 
first), and 8,900 flight cycles/20,000 flight hours (whichever occurs 
first), depending on the modification. 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-2015-4813.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM 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 
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 A300-57-6017, Revision 04, 
including Appendix 1, dated February 4, 2011. This service information 
describes procedures for repetitive inspections of certain bolt holes 
where parts of the MLG are attached to the wing rear spar, 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.

Costs of Compliance

    We estimate that this AD affects 71 airplanes of U.S. registry.
    The actions required by AD 99-16-01 and retained in this AD, take 
about 226 work-hours per product, at an average labor rate of $85 per 
work hour. Required parts cost about $0 per product. Based on these 
figures, the estimated cost of the actions that are required by AD 99-
16-01 is $19,210 per product, per inspection cycle.
    We also estimate that it will take about 226 work-hours per product 
to comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $1,363,910, or $19,210 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 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.

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) 
99-16-01, Amendment 39-11236 (64 FR 40743, July 28, 1999), and adding 
the following new AD:

2016-11-05 Airbus: Amendment 39-18532; Docket No. FAA-2015-4813; 
Directorate Identifier 2013-NM-161-AD.

(a) Effective Date

    This AD becomes effective July 15, 2016.

(b) Affected ADs

    This AD replaces AD 99-16-01, Amendment 39-11236 (64 FR 40743, 
July 28, 1999) (``AD 99-16-01'').

(c) Applicability

    This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and 
B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model 
A300 F4-605R airplanes; and Model A300 C4-605R Variant F airplanes; 
certificated in any category; all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by the results of a full-scale fatigue test 
when cracking was found on the rear spar of the wing, and the 
subsequent determination that the risk of such cracking is higher 
than initially determined. We are issuing this AD to detect and 
correct cracking of the rear spar of the wing, 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 Inspections and Corrective Actions, With Revised Service 
Information

    This paragraph restates the requirements of paragraphs (a), (b), 
(c), (d), (e), and (f) of AD 99-16-01 with revised service 
information and reduced thresholds and repetitive intervals, for 
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and 
Model A300 C4-605R Variant F airplanes; manufacturer serial numbers 
(MSNs) 252 through 553 inclusive; except those airplanes on which 
Airbus Modification 07601 has been accomplished prior to delivery.
    (1) Perform a high frequency eddy current (HFEC) rototest 
inspection to detect cracks in

[[Page 37490]]

certain bolt holes where the main landing gear (MLG) forward pick-up 
fitting and MLG rib 5 aft are attached to the rear spar, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 
25, 1994; or Airbus Service Bulletin A300-57-6017, Revision 04, 
including Appendix 1, dated February 24, 2011. As of the effective 
date of this AD, only Airbus Service Bulletin A300-57-6017, Revision 
04, including Appendix 1, dated February 24, 2011, may be used for 
the actions required by this paragraph.
    (i) For airplanes that have accumulated 17,300 total landings or 
less as of November 9, 1995 (the effective date of AD 95-20-02, 
Amendment 39-9380 (60 FR 52618, October 10, 1995)) (``AD 95-20-
02''): Inspect prior to the accumulation of 17,300 total landings, 
or within 1,500 landings after November 9, 1995, whichever occurs 
later.
    (ii) For airplanes that have accumulated 17,301 or more total 
landings, but less than 19,300 total landings as of November 9, 1995 
(the effective date of AD 95-20-02): Inspect within 1,500 landings 
after November 9, 1995.
    (iii) For airplanes that have accumulated 19,300 or more total 
landings as of November 9, 1995 (the effective date of AD 95-20-02): 
Inspect within 750 landings after November 9, 1995 (the effective 
date of AD 95-20-02).
    (2) If no crack is found during the inspection required by 
paragraph (g)(1) of this AD, repeat that inspection thereafter at 
the time specified in either paragraph (g)(2)(i) or (g)(2)(ii) of 
this AD, as applicable.
    (i) For airplanes on which Airbus Modification 07716 (as 
specified in Airbus Service Bulletin A300-57-6020) has not been 
accomplished: Inspect at the time specified in paragraph 
(g)(2)(i)(A) or (g)(2)(i)(B) of this AD, as applicable.
    (A) For airplanes having MSNs 465 through 553 inclusive: Repeat 
the inspection at intervals not to exceed 13,000 landings, until the 
inspection required by paragraph (g)(4)(ii)(A)(1) of this AD has 
been accomplished.
    (B) For airplanes having MSNs 252 through 464 inclusive: Repeat 
the inspection at intervals not to exceed 8,400 landings, until the 
inspection required by paragraph (g)(4)(ii)(A)(2) of this AD has 
been accomplished.
    (ii) For airplanes on which Airbus Modification 07716 has been 
accomplished: Inspect at the time specified in either paragraph 
(g)(2)(ii)(A) or (g)(2)(ii)(B) of this AD, as applicable.
    (A) For airplanes having MSNs 465 through 553 inclusive: Repeat 
the inspection at intervals not to exceed 11,800 landings, until the 
inspection required by paragraph (g)(4)(i)(B) of this AD has been 
accomplished.
    (B) For airplanes having MSNs 252 through 464 inclusive: Repeat 
the inspection within 10,700 landings following the initial 
inspection required by paragraph (g)(1) of this AD, and thereafter 
at intervals not to exceed 7,500 landings, until the inspection 
required by paragraph (g)(4)(ii)(B)(2) has been accomplished.
    (3) If any crack is found during the inspection required by 
either paragraph (g)(1) or (g)(2) of this AD, prior to further 
flight, accomplish the requirements of either paragraph (g)(3)(i) or 
(g)(3)(ii) of this AD, as applicable.
    (i) For airplanes on which Airbus Modification 07716 has not 
been accomplished: Oversize the bolt hole by 1/32 inch and repeat 
the HFEC inspection required by paragraph (g)(1) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 
25, 1994. After accomplishing the oversizing and HFEC inspection, 
repeat the inspection, as required by paragraph (g)(2) of this AD, 
at the applicable schedule specified in that paragraph, until the 
inspection required by paragraph (g)(4)(ii)(B)(1) or 
(g)(4)(ii)(B)(2) of this AD has been accomplished.
    (A) If no cracking is detected, install the second oversize bolt 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6017, Revision 01, including Appendix 1, dated July 
25, 1994.
    (B) If any cracking is detected, repair in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.
    (ii) For airplanes on which Airbus Modification 07716 has been 
accomplished: Repair in accordance with a method approved by the 
Manager, International Branch, ANM-116. After repair, repeat the 
inspections as required by paragraph (g)(2) of this AD at the 
applicable schedule specified in that paragraph, until the 
inspection required by paragraph (g)(4)(ii)(B)(1) or 
(g)(4)(ii)(B)(2) of this AD has been accomplished.
    (4) Perform an ultrasonic inspection to detect cracks in certain 
bolt holes where the MLG forward pick-up fitting and MLG rib 5 aft 
are attached to the rear spar, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6017, Revision 03, 
dated November 19, 1997; or Revision 04, including Appendix 1, dated 
February 24, 2011; at the time specified in paragraph (g)(4)(i) or 
(g)(4)(ii) of this AD, as applicable. As of the effective date of 
this AD, only Airbus Service Bulletin A300-57-6017, Revision 04, 
including Appendix 1, dated February 24, 2011, may be used for the 
actions in this paragraph.
    (i) For airplanes not inspected prior to September 1, 1999 (the 
effective date of AD 99-16-01), as specified in Airbus Service 
Bulletin A300-57-6017, dated November 22, 1993; or Revision 01, 
including Appendix 1, dated July 25, 1994: Inspect at the time 
specified in paragraph (g)(4)(i)(A), (g)(4)(i)(B), or (g)(4)(i)(C) 
of this AD, as applicable. Accomplishment of this inspection 
terminates the requirements of paragraph (g)(1) of this AD.
    (A) For airplanes that have accumulated 17,300 total landings or 
fewer as of the effective date of this AD: Inspect prior to the 
accumulation of 17,300 total landings, or within 1,500 landings 
after September 1, 1999 (the effective date of AD 99-16-01), 
whichever occurs later.
    (B) For airplanes that have accumulated 17,301 total landings or 
more but fewer than 19,300 total landings as of September 1, 1999 
(the effective date of AD 99-16-01): Inspect within 1,500 landings 
after September 1, 1999 (the effective date of AD 99-16-01).
    (C) For airplanes that have accumulated 19,300 total landings or 
more as of September 1, 1999 (the effective date of AD 99-16-01): 
Inspect within 750 landings after September 1, 1999 (the effective 
date of AD 99-16-01).
    (ii) For airplanes on which an HFEC inspection was performed 
prior to September 1, 1999 (the effective date of AD 99-16-01), in 
accordance with the requirements of paragraph (g)(1) of this AD, or 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6017, dated November 22, 1993: Inspect at the time 
specified in paragraph (g)(4)(ii)(A) or (g)(4)(ii)(B) of this AD, as 
applicable.
    (A) If no cracking was detected during any HFEC inspection 
accomplished prior to September 1, 1999 (the effective date of AD 
99-16-01), and if Airbus Modification 07716 has not been 
accomplished: Inspect at the time specified in paragraph 
(g)(4)(ii)(A)(1) or (g)(4)(ii)(A)(2) of this AD, as applicable.
    (1) For airplanes having MSNs 465 through 553 inclusive: Inspect 
within 13,000 landings after the most recent HFEC inspection, and 
thereafter at intervals not to exceed 8,900 landings. Accomplishment 
of this inspection constitutes terminating action for the repetitive 
inspection requirement of paragraph (g)(2)(i)(A) of this AD.
    (2) For airplanes having MSNs 252 through 464 inclusive: Inspect 
within 8,400 landings after the most recent HFEC inspection, and 
thereafter at intervals not to exceed 5,500 landings. Accomplishment 
of this inspection constitutes terminating action for the repetitive 
inspection requirement of paragraph (g)(2)(i)(B) of this AD.
    (B) If any cracking was detected during any HFEC inspection 
performed prior to the effective date of this AD, regardless of the 
method of repair, or if Airbus Modification 07716 has been 
accomplished: Inspect at the time specified in paragraph 
(g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of this AD, as applicable.
    (1) For airplanes having MSNs 465 through 553 inclusive: Inspect 
within 11,800 landings after the most recent HFEC inspection, and 
thereafter at intervals not to exceed 8,200 landings. Accomplishment 
of this inspection constitutes terminating action for the repetitive 
inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this 
AD, as applicable.
    (2) For airplanes having MSNs 252 through 464 inclusive: Inspect 
within 10,700 landings after the initial inspection in accordance 
with paragraph (g)(1) of this AD, or within 7,500 landings after the 
most recent HFEC inspection, whichever occurs later, and thereafter 
at intervals not to exceed 4,900 landings. Accomplishment of this 
inspection constitutes terminating action for the repetitive 
inspection requirement of paragraph (g)(3)(i) or (g)(3)(ii) of this 
AD, as applicable.
    (5) If no cracking is detected during the ultrasonic inspection 
required by paragraph (g)(4)(i) of this AD, repeat that inspection 
thereafter at the time specified in paragraph (g)(5)(i) or 
(g)(5)(ii) of this AD, as applicable, until the initial ultrasonic 
inspection required by paragraph (h) of this AD is done.

[[Page 37491]]

    (i) For airplanes having MSNs 465 through 553 inclusive: Repeat 
the inspection at intervals not to exceed 8,900 landings.
    (ii) For airplanes having MSNs 232 through 464 inclusive: Repeat 
the inspection at intervals not to exceed 5,500 landings.
    (6) If any cracking is detected during any inspection performed 
in accordance with the requirements of paragraph (g)(4) or (g)(5) of 
this AD: Prior to further flight, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116; or the 
Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its 
delegated agent); or the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA).

    Note 1 to paragraph (g) of this AD:  Airbus Service Bulletin 
A300-57-6017, Revision 01, including Appendix 1, dated July 25, 
1994; and Airbus Service Bulletin A300-57-6017, Revision 04, 
including Appendix 1, dated February 24, 2011; also reference Airbus 
Service Bulletin A300-57-6020, dated November 22, 1993, as an 
additional source of service information for installation of 
oversize studs in the bolt holes.

(h) New Repetitive Inspections

    At the applicable times specified in paragraph 1.B.(5), 
``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-
6017, Revision 04, including Appendix 1, dated February 24, 2011: Do 
ultrasonic inspections to detect cracks in the MLG attachment 
fitting holes on the wing rear spar, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6017, 
Revision 04, including Appendix 1, dated February 24, 2011. Repeat 
the inspections thereafter at the applicable intervals specified in 
paragraph 1.B.(5), ``Accomplishment Timescale,'' of Airbus Service 
Bulletin A300-57-6017, Revision 04, including Appendix 1, dated 
February 24, 2011. For airplanes modified as specified in Airbus 
Service Bulletin A300-57-6073, the initial inspection threshold is 
counted from the completion date of the modification. Clarification 
of compliance time terminology used in table 1, ``Structural 
Inspection Program,'' of Airbus Service Bulletin A300-57-6017, 
Revision 04, including Appendix 1, dated February 24, 2011, is 
provided in paragraphs (h)(1) through (h)(4) of this AD. 
Accomplishment of the initial inspection terminates the repetitive 
inspections required by paragraph (g)(5) of this AD.
    (1) For pre-Airbus Modification 07716 or pre-Airbus Modification 
11440 airplanes:
    (i) The term ``flight cycles'' in the ``Inspection Threshold'' 
column is total flight cycles accumulated by the airplane.
    (ii) The term ``flight hours'' in the ``Inspection Threshold'' 
column is total flight hours accumulated by the airplane.
    (2) For post-Airbus Modification 07716 airplanes:
    (i) The term ``flight cycles'' in the ``Inspection Threshold'' 
column is total flight cycles accumulated by the airplane.
    (ii) The term ``flight hours'' in the ``Inspection Threshold'' 
column is total flight hours accumulated by the airplane.
    (3) For post-Airbus Modification 11440 (Airbus Service Bulletin 
A300-57-6073) airplanes:
    (i) The term ``flight cycles'' in the ``Inspection Threshold'' 
column is flight cycles accumulated by the airplane after the 
modification was done.
    (ii) The term ``flight hours'' in the ``Inspection Threshold'' 
column is flight hours accumulated by the airplane after the 
modification was done.
    (4) For post-Airbus Modification 07601 airplanes:
    (i) The term ``flight cycles'' in the ``Inspection Threshold'' 
column is total flight cycles accumulated by the airplane.
    (ii) The term ``flight hours'' in the ``Inspection Threshold'' 
column is total flight hours accumulated by the airplane.

(i) Repairs

    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 the EASA; or Airbus's EASA 
DOA.

(j) Non-Terminating Repair

    Accomplishment of any repair as required by paragraph (i) of 
this AD is not terminating action for the repetitive inspections 
required by paragraph (g) or (h) of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using any of the following 
service information.
    (1) Airbus Service Bulletin A300-57-6017, dated November 22, 
1993, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-57-6017, Revision 01, including 
Appendix 1, dated July 25, 1994, which was incorporated by reference 
in AD 95-20-02 and is retained in this AD.
    (3) Airbus Service Bulletin A300-57-6017, Revision 02, dated 
January 14, 1997, including Appendix 1, dated July 25, 1994, which 
is not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A300-57-6017, Revision 03, including 
Appendix 1, dated November 19, 1997, which was incorporated by 
reference in AD 99-16-01, but is not retained in this AD.

(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 99-16-01 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0180, dated August 9, 2013, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov searching for and 
locating Docket No. FAA-2015-4813.
    (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 
July 15, 2016.
    (i) Airbus Service Bulletin A300-57-6017, Revision 04, including 
Appendix 1, dated February 24, 2011.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
November 9, 1995 (60 FR 52618, October 10, 1995).
    (i) Airbus Service Bulletin A300-57-6017, Revision 01, including 
Appendix 1, dated July 25, 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

[[Page 37492]]

202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 18, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-12324 Filed 6-9-16; 8:45 am]
 BILLING CODE 4910-13-P