Document ID: FAA-2016-0451-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2016-02-01T05:00Z

[Federal Register Volume 81, Number 20 (Monday, February 1, 2016)]
[Proposed Rules]
[Pages 5056-5060]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01736]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 81, No. 20 / Monday, February 1, 2016 / 
Proposed Rules  

[[Page 5056]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0451; Directorate Identifier 2013-NM-253-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2004-23-
20 for certain Airbus Model A300 series airplanes and Model A300 B4-
601, A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, 
A300 F4-605R, and C4-605R Variant F airplanes. AD 2004-23-20 currently 
requires, for certain airplanes, repetitive inspections for cracking 
around certain attachment holes, installation of new fasteners for 
certain airplanes, and follow-on corrective actions if necessary. AD 
2004-23-20 also requires modifying certain fuselage frames, which 
terminates certain repetitive inspections. Since we issued AD 2004-23-
20, we received a report indicating that the material used to 
manufacture the upper frame feet was changed and negatively affected 
the fatigue life of the frame feet. This proposed AD would reduce the 
compliance times for the initial inspection and the inspection 
intervals. This proposed AD would also expand the applicability and 
require an additional repair on certain airplanes that have been 
modified. We are proposing this AD to prevent cracking of the center 
section of the fuselage, which could result in a ruptured frame foot 
and reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by March 17, 2016.

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 NPRM, 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-2016-
0451; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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, 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-2016-0451; 
Directorate Identifier 2013-NM-253-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 November 10, 2004, we issued AD 2004-23-20, Amendment 39-13875 
(69 FR 68779, November 26, 2004) for all Airbus Model A300 series 
airplanes and Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-622, 
A300 B4-605R, A300 B4-622R, A300 F4-605R and A300 C4-605R Variant F 
airplanes. (That AD superseded AD 2001-06-10, Amendment 39-12157 (66 FR 
17490, April 2, 2001)). AD 2004-23-20 requires actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2004-23-20, Amendment 39-13875 (69 FR 68779, 
November 26, 2004) we received a report indicating that a change in 
material for manufacturing the frame feet for certain airplanes 
negatively impacted the fatigue life of the frame feet.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0295, dated December 11, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for Airbus Model A300 B4-
601, A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, 
A300 F4-605R, and A300 C4-605R Variant F airplanes. The MCAI states:

    During a scheduled inspection of the fuselage frame feet of an 
in-service A300-600 aeroplane, cracks were observed in Frame (FR) 
43, FR 44, FR 45 and FR 46 between stringer (STGR) 24 and STGR 30.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.

[[Page 5057]]

    To address this unsafe condition, [Direction Generale de 
l'Aviation Civile] DGAC France issued [an] AD * * * to require 
repetitive inspections of the affected frames and stringers on both 
sides of the fuselage and, depending on findings, repairs, as 
specified in Airbus Service Bulletin (SB) A300-53-6122.
    Subsequently, DGAC France issued AD F-2004-002 [http://ad.easa.europa.eu/ad/F-2004-002] (EASA approval 2003-2108) [which 
corresponds to FAA AD 2004-23-20, Amendment 39-13875 (69 FR 68779, 
November 26, 2004)], retaining the requirements of [an] AD * * * and 
required the embodiment of Airbus SB A300-53-6125 (Airbus 
modification 12168) in order to improve the life of the frame foot 
attachment.
    Since DGAC France AD F-2004-002 was issued, 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.
    It was highlighted that the frame feet material change from 
2024T3511 (A300B4) to 7175T7351 (A300-600) had an impact on the 
frame feet fatigue life duration. Airbus SB A300-53-6122 was revised 
accordingly to decrease the inspection thresholds and intervals. 
Subsequent SB revision introduced a second structural modification 
point (SMP2) for aeroplanes that embody Airbus SB A300-53-6125 
(modification 12168).
    For the reasons described above, this new [EASA] AD retains the 
requirements of DGAC France AD F-2004-002, which is superseded, but 
requires those actions within the new thresholds and intervals as 
specified in Revision 04 of Airbus SB A300-53-6122.

    The retained requirements include rototest inspections for cracking 
in the area surrounding the frame feet attachment holes between 
fuselage FR 41 and FR 46 from stringers 24 to 28 on the left and right 
sides, and related investigative and corrective action if necessary. 
The related investigative actions include additional rotating probe 
inspections of the adjacent holes. The corrective actions include 
reaming out cracks, cold working fastener holes, and installing 
oversized fasteners, or repair. This proposed AD also expands the 
applicability to include airplanes on which Airbus Modification 12168 
was done. You may examine the MCAI in the AD docket on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2016-0451.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-53-6122, Revision 04, dated 
February 27, 2012. The service information describes procedures for the 
repetitive inspections of certain frame feet attachment holes for 
cracks, installation of new fasteners, and repair of cracked areas.
    In addition, Airbus has issued Service Bulletin A300-53-6125, 
Revision 01, dated June 13, 2003. The service information provides 
compliance times for certain airplanes to do the proposed modification.
    Airbus has also issued Service Bulletin A300-53-6125, Revision 04, 
dated March 17, 2015. The service information describes procedures for 
the modification of certain upper frame feet fittings.
    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.

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.

Changes to AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 
2004)

    This proposed AD would retain all requirements of AD 2004-23-20, 
Amendment 39-13875 (69 FR 68779, November 26, 2004). Since AD 2004-23-
20 was issued the AD format has been revised, and certain paragraphs 
have been rearranged. As a result, the corresponding paragraph 
designators have changed in this proposed AD, as listed in the 
following table:

                      Revised Paragraph Designators
------------------------------------------------------------------------
   Requirement in AD 2004-23-20,
  Amendment 39-13875 (69 FR 68779,    Corresponding requirement in this
         November 26, 2004)                      proposed AD
------------------------------------------------------------------------
             paragraph (f)                       paragraph (g).
             paragraph (g)                       paragraph (h).
             paragraph (h)                       paragraph (i).
             paragraph (i)                       paragraph (j).
             paragraph (j)                       paragraph (k).
------------------------------------------------------------------------

    We have converted ``TABLE 1.--SERVICE INFORMATION'' in AD 2004-23-
20, Amendment 39-13875 (69 FR 68779, November 26, 2004) to text in 
paragraphs (j)(3)(i) and (j)(3)(ii) of this proposed AD for formatting 
purposes only.
    We have also moved the service information acceptable for 
compliance if previously done from ``TABLE 1.--SERVICE INFORMATION'' in 
AD 2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004) to 
paragraph (r)(2) of this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 65 airplanes of U.S. 
registry.
    The actions that are required by AD 2004-23-20, Amendment 39-13875 
(69 FR 68779, November 26, 2004), and retained in this proposed AD take 
about 90 work-hours per product, at an average labor rate of $85 per 
work-hour. Required parts cost about $4,000 per product. Based on these 
figures, the estimated cost of the actions that were required by AD 
2004-23-20 is $11,650 per product.
    We also estimate that it would take up to 109 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost up 
to $6,070 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $996,775, or $15,335 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

[[Page 5058]]

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

Airbus: Docket No. FAA-2016-0451; Directorate Identifier 2013-NM-
253-AD.

(a) Comments Due Date

    We must receive comments by March 17, 2016.

(b) Affected ADs

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

(c) Applicability

    This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 airplanes; and Model A300 B4-601, 
A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, 
A300 F4-605R and A300 C4-605R Variant F airplanes; certificated in 
any category, all manufacturer serial numbers.

(d) Subject

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

(e) Reason

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

(f) Compliance

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

(g) Retained Inspections

    This paragraph restates the requirements of paragraph (f) of AD 
2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), 
with revised service information. For Model A300 B4-600 and A300 B4-
600R series airplanes, and Model A300 C4-605R Variant F and A300 F4-
605R airplanes, except those airplanes modified by Airbus 
Modification 12168: Perform a high-frequency eddy-current or 
rototest inspection to detect cracking in the area surrounding the 
frame feet attachment holes between fuselage frames (FR) 41 and FR 
46 from stringers 24 to 28, left-and right-hand sides, in accordance 
with Airbus Service Bulletin A300-53-6122, dated February 9, 2000; 
or the Accomplishment Instructions of Airbus Service Bulletin A300-
53-6122, Revision 04, dated February 27, 2012; at the applicable 
time specified in paragraph (g)(1) or (g)(2) of this AD. 
Accomplishing an inspection required by paragraph (m) of this AD 
terminates the inspections required by this paragraph.
    (1) For airplanes on which Task 53-15-54 in Maintenance Review 
Board Document (MRBD), Revision 3, dated April 1998, has not been 
accomplished as of May 7, 2001 (the effective date of AD 2001-06-10, 
Amendment 39-12157 (66 FR 17490, April 2, 2001)): Perform the 
inspection at the later of the times specified in paragraphs 
(g)(1)(i) and (g)(1)(ii) of this AD.
    (i) Prior to the accumulation of the total flight-cycle or 
flight-hour threshold, whichever occurs first, specified in 
paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-
6122, dated February 9, 2000; or
    (ii) Within the applicable grace period specified in paragraph 
1.E. (``Compliance'') of Airbus Service Bulletin A300-53-6122, dated 
February 9, 2000.
    (2) For airplanes on which Task 53-15-54 in the MRBD, Revision 
3, dated April 1998, has been accomplished as of May 7, 2001 (the 
effective date of AD 2001-06-10, Amendment 39-12157 (66 FR 17490, 
April 2, 2001)): Perform the next repetitive inspection at the later 
of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of 
this AD.
    (i) Within the flight-cycle or flight-hour interval, whichever 
occurs first, specified in paragraph 1.E. (``Compliance'') of Airbus 
Service Bulletin A300-53-6122, dated February 9, 2000, following the 
latest inspection accomplished as specified in MRBD, Revision 3, 
dated April 1998; or
    (ii) Within the grace period specified in paragraph 1.E. 
(``Compliance'') of Airbus Service Bulletin A300-53-6122, dated 
February 9, 2000.

(h) Retained Installation of Fasteners and Repetitive Inspections

    This paragraph restates the requirements of paragraph (g) of AD 
2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), 
with revised service information. For airplanes on which no cracking 
is detected during the inspection required by paragraph (g) of this 
AD, prior to further flight, install new fasteners as applicable, in 
accordance with Airbus Service Bulletin A300-53-6122, dated February 
9, 2000; or the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6122, Revision 04, dated February 27, 2012; and 
repeat the inspection required by paragraph (g) of this AD 
thereafter at intervals not to exceed the applicable intervals 
specified in paragraph 1.E. (``Compliance'') of Airbus Service 
Bulletin A300-53-6122, dated February 9, 2000; until the actions 
required by paragraph (j) or (o) of this AD have been done or the 
initial inspection required by paragraph (m) of this AD is done.

(i) Retained Corrective Actions

    This paragraph restates the requirements of paragraph (h) of AD 
2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), 
with revised service information. For airplanes on which cracking is 
detected during any inspection required by paragraph (g) of this AD: 
Prior to further flight, except as required by paragraph (k) of this 
AD, accomplish corrective actions (e.g., performing rotating probe 
inspections, reaming out cracks, cold working fastener holes, and 
installing oversized fasteners) in accordance with Airbus Service 
Bulletin A300-53-6122, dated February 9, 2000; or the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6122, Revision 04, 
dated February 27, 2012. Repeat the inspection required by paragraph 
(g) of this AD thereafter at intervals not to exceed the applicable 
intervals specified in paragraph 1.E. (``Compliance'') of Airbus 
Service Bulletin A300-53-6122, dated February 9, 2000; until the 
actions required by paragraph (j) or (o) of this AD have been done, 
or the initial inspection required by paragraph (m) of this AD is 
done.

(j) Retained Modification: Model A300 Series Airplanes

    This paragraph restates the requirements of paragraph (i) of AD 
2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), for 
certain airplanes, with no changes. For Model A300 series airplanes: 
Within the compliance times specified in paragraph 1.E. 
(``Compliance'') of Airbus Service Bulletin A300-53-0271, Revision 
03, dated June 13, 2003, modify the fuselage frames, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-53-0271, Revision 03, dated June 13, 2003. For airplanes that 
have exceeded their design service goal, as specified in NOTE (01) 
of paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-
53-0271, Revision 03, dated June 13, 2003; this AD requires 
compliance within the earlier of the flight-cycle and flight-hour 
grace periods specified in Airbus Service Bulletin A300-53-0271, 
Revision 03, dated June 13, 2003.

[[Page 5059]]

(k) Retained Exceptions to Service Bulletin Procedures

    This paragraph restates the requirements of paragraph (j) of AD 
2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004), 
with specific delegation approval language. During any inspection 
required by paragraphs (g), (h), (i), or (j) of this AD, if the 
applicable service information specified in paragraphs (g), (h), 
(i), and (j) of this AD specifies to contact the manufacturer for 
appropriate instructions: Before further flight, perform all 
applicable corrective actions in accordance with a method approved 
by the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the Direction Generale de l'Aviation Civile 
(DGAC) (or its delegated agent); or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).

(l) New Definition for This AD: Average Flight Time (AFT)

    For the purpose of this AD, use the parameters specified in 
paragraphs (l)(1), (l)(2), and (l)(3) of this AD to determine the 
applicable AFT for the actions required by paragraph (m) and 
compliance times required by paragraph (n) of this AD.
    (1) The initial inspection compliance time, as the total 
accumulated flight hours counted from take-off to touch-down, 
divided by the total accumulated flight cycles as of the effective 
date of this AD.
    (2) The first repetitive inspection interval, as the total 
accumulated flight hours divided by the total accumulated flight 
cycles at the time of the inspection.
    (3) The second inspection interval and subsequent, as the flight 
hours divided by the flight cycles between the last two inspections.

(m) New Requirements of This AD: Inspections and Corrective Actions

    (1) At the applicable time specified in paragraph (n)(1) of this 
AD, do a rotating probe inspection for discrepancies of the frame 
feet attachment holes from FR 41 through FR 46, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
6122, Revision 04, dated February 27, 2012. Repeat the inspections 
thereafter at intervals not to exceed those specified in paragraph 
(n)(2) of this AD. Accomplishment of this inspection terminates the 
inspections required by paragraph (g)(2) of this AD.
    (2) If any discrepancy (e.g., cracking or damage) is found 
during any inspection required by paragraph (m)(1) of this AD, 
before further flight, do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6122, Revision 04, 
dated February 27, 2012; except where Airbus Service Bulletin A300-
53-6122, Revision 04, dated February 27, 2012, specifies to contact 
Airbus, 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.
    (3) Corrective actions, as required by paragraph (m)(2) of this 
AD, do not constitute terminating action for the repetitive 
inspections required by paragraph (m)(1) of this AD.

(n) Compliance Times for Initial and Repetitive Inspections

    (1) Do the initial rotating probe inspection required by 
paragraph (m)(1) of this AD at the applicable times specified in 
paragraphs (n)(1)(i), (n)(1)(ii), and (n)(1)(iii) of this AD; or 
within 1,000 flight cycles after the effective date of this AD; 
whichever occurs later.
    (i) For airplanes on which the modification specified in Airbus 
Service Bulletin A300-53-6125 has not been done as of the effective 
date of this AD: At the applicable times specified in paragraph 
(n)(1)(i)(A) or (n)(1)(i)(B) of this AD.
    (A) If the AFT is greater than 1.5 flight hours/flight cycles: 
Within 14,800 flight hours or 6,800 flight cycles, whichever occurs 
first, since the airplane's first flight.
    (B) If the AFT is less than or equal to 1.5 flight hours/flight 
cycles: Within 11,100 flight hours or 7,400 flight cycles, whichever 
occurs first, since the airplane's first flight.
    (ii) For airplanes on which the modification specified in Airbus 
Service Bulletin A300-53-6125 has been done as of the effective date 
of this AD, except as provided by paragraph (n)(1)(iii) of this AD: 
At the applicable times specified in paragraph (n)(1)(ii)(A) or 
(n)(1)(ii)(B) of this AD.
    (A) If the AFT is greater than 1.5 flight hours/flight cycles: 
Within 56,400 flight hours or 26,100 flight cycles, whichever occurs 
first, after doing the modification specified in Airbus Service 
Bulletin A300-53-6125.
    (B) If the AFT is less than or equal to 1.5 flight hours/flight 
cycles: Within 42,300 flight hours or 28,200 flight cycles, 
whichever occurs first, after doing the modification specified in 
Airbus Service Bulletin A300-53-6125.
    (iii) For airplanes on which the additional modification 
required by paragraph (p) of this AD has been done: At the 
applicable times in paragraph (n)(1)(iii)(A) or (n)(1)(iii)(B) of 
this AD.
    (A) If the AFT is greater than 1.5 flight hours/flight cycles: 
Within 69,400 flight hours or 32,100 flight cycles, whichever occurs 
first, after doing the modification specified in Airbus Service 
Bulletin A300-53-6125.
    (B) If the AFT is less than or equal to 1.5 flight hours/flight 
cycles: Within 52,000 flight hours or 34,700 flight cycles, 
whichever occurs first, after doing the modification specified in 
Airbus Service Bulletin A300-53-6125.
    (2) Do the repetitive rotating probe inspections required by 
paragraph (m)(1) of this AD at intervals not to exceed those 
specified in paragraph (n)(2)(i) or (n)(2)(ii) of this AD, as 
applicable.
    (i) If the AFT is greater than 1.5 flight hours/flight cycles: 
7,800 flight hours or 3,600 flight cycles, whichever occurs first.
    (ii) If the AFT is less than or equal to 1.5 flight hours/flight 
cycles: 5,800 flight hours or 3,900 flight cycles, whichever occurs 
first.

(o) New Requirement of This AD: Modification for Model A300 B4-601, 
A300 B4-603, A300 B4-620, A300 B4-622, A300 B4-605R, A300 B4-622R, A300 
F4-605R and A300 C4-605R Variant F Airplanes

    (1) For Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-
622, A300 B4-605R, A300 B4-622R, A300 F4-605R and A300 C4-605R 
Variant F airplanes, except those modified in production before the 
effective date of this AD by Airbus Modification 12168 or those on 
which the modification (i.e., reinforcement of the upper frame feet 
fittings) specified in the service information identified in 
paragraph (p)(1)(i), (p)(1)(ii), or (p)(1)(iii) of this AD has been 
done before the effective date of this AD: At the applicable time 
specified in paragraph (o)(1)(i) or (o)(1)(ii) of this AD: Reinforce 
the upper frame feet fittings, including doing all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6125, 
Revision 04, dated March 17, 2015, except where Airbus Service 
Bulletin A300-53-6125, Revision 04, dated March 17, 2015, specifies 
to contact Airbus, 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. Do all 
applicable related investigative and corrective actions before 
further flight.
    (i) For airplanes with an AFT greater than 1.5 flight hours/
flight cycles as of the effective date of this AD: At the later of 
the times in paragraphs (o)(1)(i)(A) and (o)(1)(i)(B) of this AD:
    (A) Within 18,200 flight hours or 8,400 flight cycles, whichever 
occurs first, since the airplane's first flight; or
    (B) At the earlier of the times specified in paragraphs 
(o)(1)(i)(B)1 and (o)(1)(i)(B)2 of this AD.
    1 Within 1,000 flight cycles after the effective date of this 
AD.
    2 Within the compliance times specified in paragraph 1.E. 
(``Compliance'') of Airbus Service Bulletin A300-53-6125, Revision 
01, dated June 13, 2003. For airplanes that have exceeded their 
design service goal, as specified in NOTE (01) of paragraph 1.E. 
(``Compliance'') of Airbus Service Bulletin A300-53-6125, Revision 
01, dated June 13, 2003; within the earlier of the flight-cycle and 
flight-hour grace periods specified in Airbus Service Bulletin A300-
53-6125, Revision 01, dated June 13, 2003.
    (ii) For airplanes with an AFT less than or equal to 1.5 flight 
hours/flight cycles as of the effective date of this AD: At the 
later of the times in paragraphs (o)(1)(ii)(A) and (o)(1)(ii)(B) of 
this AD:
    (A) Within 13,700 flight hours or 9,100 flight cycles, whichever 
occurs first, since the airplane's first flight; or
    (B) At the earlier of the times specified in paragraphs 
(o)(1)(ii)(B)1 and (o)(1)(ii)(B)2 of this AD.
    1 Within 1,000 flight cycles after the effective date of this AD
    2 Within the compliance times specified in paragraph 1.E. 
(``Compliance'') of Airbus Service Bulletin A300-53-6125, Revision 
01, dated June 13, 2003. For airplanes that have

[[Page 5060]]

exceeded their design service goal, as specified in NOTE (01) of 
paragraph 1.E. (``Compliance'') of Airbus Service Bulletin A300-53-
6125, Revision 01, dated June 13, 2003; within the earlier of the 
flight-cycle and flight-hour grace periods specified in Airbus 
Service Bulletin A300-53-6125, Revision 01, dated June 13, 2003.
    (2) For the affected Model A300 B4-600 series airplanes: 
Accomplishment of the modification specified in Airbus Service 
Bulletin A300-53-6125 before the effective date of this AD 
terminates the requirements of paragraphs (g), (h), and (i) of this 
AD.
    (3) For Model A300 B2 and A300 B4 series airplanes: 
Accomplishment of the modification specified in Airbus Service 
Bulletin A300-53-6125 terminates certain repetitive inspections 
required by AD 2007-04-11, Amendment 39-14943 (72 FR 8604, February 
27, 2014), i.e., inspections of the frame feet holes for frames 41 
to 46 (as specified in Airbus Service Bulletin A300-53-0345) and 
frames 48 to 54 (as specified in Airbus Service Bulletin A300-53-
238). However, the repetitive inspections of the frame foot angle 
radius (as specified in Service Bulletin A300-53-238), which are 
required by AD 2007-04-11, must continue.

(p) New Requirement of This AD: Additional Modification for Certain 
Airplanes

    (1) For Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-
622, A300 B4-605R, A300 B4-622R, A300 F4-605R and A300 C4-605R 
Variant F airplanes modified in production before the effective date 
of this AD by Airbus Modification 12168, or modified before the 
effective date of this AD by accomplishment of the reinforcement of 
the upper frame feet fittings specified in the service information 
identified in paragraph (p)(1)(i), (p)(1)(ii), or (p)(1)(iii) of 
this AD: Within 360 flight cycles prior to reaching the applicable 
compliance time specified in paragraph (p)(2)(i) or (p)(2)(ii) of 
this AD, contact the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; 
for modification instructions and within the applicable compliance 
time specified in paragraph (p)(2) of this AD, do the modification 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA 
DOA.
    (i) Airbus Service Bulletin A300-53-6125, dated November 8, 
2000.
    (ii) Airbus Service Bulletin A300-53-6125, Revision 01, dated 
June 13, 2003,
    (iii) Airbus Service Bulletin A300-53-6125, Revision 02, dated 
February 25, 2005.
    (2) Do the modification required by paragraph (p)(1) of this AD 
at the applicable time specified below.
    (i) For airplanes with an AFT greater than 1.5 flight hours/
flight cycles as of the effective date of this AD: Within 32,100 
flight cycles after the modification was completed.
    (ii) For airplanes with an AFT less than or equal to 1.5 flight 
hours/flight cycles as of the effective date of this AD: Within 
34,700 flight cycles after the modification was completed.

(q) Modification Is Not Terminating Action

    Accomplishment of the modification specified in paragraph (o) or 
(p) of this AD does not constitute terminating action for the 
repetitive inspections required by paragraph (m)(1) of this AD.

(r) Credit for Previous Actions

    (1) For Model A300 B4-600 and B4-600R series airplanes, and 
Model A300 C4-605R Variant F and A300 F4-605R airplanes: This 
paragraph provides credit for inspections and corrective actions 
required by paragraphs (g), (h), and (i) of this AD, if those 
actions were performed before the effective date of this AD using 
the applicable service information specified in paragraphs 
(r)(1)(i), (r)(1)(ii), and (r)(1)(iii) of this AD.
    (i) Airbus Service Bulletin A300-53-6122, Revision 01, dated 
September 5, 2001, which is not incorporated by reference in this 
AD.
    (ii) Airbus Service Bulletin A300-53-6122, Revision 02, dated 
June 17, 2002, which is not incorporated by reference in this AD.
    (iii) Airbus Service Bulletin A300-53-6122, Revision 03, dated 
August 25, 2011, which is not incorporated by reference in this AD.
    (2) This paragraph restates the credit for Airbus Model A300 
series airplanes for previous actions as provided by Table 1 of AD 
2004-23-20, Amendment 39-13875 (69 FR 68779, November 26, 2004). For 
Airbus Model A300 series airplanes: This paragraph provides credit 
for actions required by paragraph (j) of this AD, if those actions 
were performed before January 3, 2005 (the effective date of AD 
2004-23-20) using the service information specified in paragraph 
(r)(2)(i), (r)(2)(ii), or (r)(2)(iii) of this AD.
    (i) Airbus Service Bulletin A300-53-0271, dated September 10, 
1991, which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A300-53-0271, Revision 01, dated 
February 16, 1993, which is not incorporated by reference in this 
AD.
    (iii) Airbus Service Bulletin A300-53-0271, Revision 02, dated 
July 13, 2000, which is not incorporated by reference in this AD.

(s) 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, 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 96-13-11, Amendment 39-
9679 (61 FR 35122, July 5, 1996), and AD 2001-06-10, Amendment 39-
12157, April 2, 2001), are approved as AMOCs for the corresponding 
requirements 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' EASA DOA. If approved 
by the DOA, the approval must include the DOA-authorized signature.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0295, dated December 11, 
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-2016-0451.
    (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 January 21, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-01736 Filed 1-29-16; 8:45 am]
 BILLING CODE 4910-13-P