
[Federal Register Volume 81, Number 12 (Wednesday, January 20, 2016)]
[Proposed Rules]
[Pages 3045-3051]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00634]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8470; Directorate Identifier 2013-NM-199-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 95-21-09, 
for all Airbus Model A300 series airplanes, and 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 95-21-09 currently requires repetitive inspections for 
cracking of the No. 2 flap beams, and replacement of the flap beams, if 
necessary; and provides optional modifications for extending certain 
inspection thresholds, and an optional terminating modification for 
certain inspections. Since we issued AD 95-21-09, we have determined 
that the compliance times must be reduced. This proposed AD would 
reduce the compliance times for inspections and also reduce the number 
of airplanes affected. We are proposing this AD to detect and correct 
cracking of the No. 2 flap beams, which could result in rupture of the 
flap beams and reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by March 7, 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.

[[Page 3046]]

     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
8470; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-8470; 
Directorate Identifier 2013-NM-199-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 October 3, 1995, we issued AD 95-21-09, Amendment 39-9395 (60 FR 
53847, October 18, 1995). AD 95-21-09 requires actions intended to 
address an unsafe condition on Airbus Model A300 and A300-600 series 
airplanes.
    Since we issued AD 95-21-09, Amendment 39-9395 (60 FR 53847, 
October 18, 1995), we have received a report that analyses showed a 
need for reduced compliance times.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2013-0234R2, dated October 7, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A300 and A300-600 
series airplanes. The MCAI states:

    Fatigue and ``fail safe'' tests developed on a test specimen 
confirmed that cracks may appear and propagate from the bolt holes 
of the base member and the side members of flap beam No. 2.
    The development of such cracks, if not detected, could result in 
a rupture of flap beams No. 2, which could adversely affect the 
structural integrity of the airframe.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A300-57-0116 and SB A300-57-6005 and DGAC 
France issued AD 1986-187-076(B) [available at http://ad.easa.europa.eu/blob/1986-187-076%28B%29R4en.pdf/AD_F-1986-187-076R4_1], later revised, to require a repetitive inspection 
programme [and corrective action] for A300 and A300-600 aeroplanes. 
[French AD 86-187-076(B)R3, dated March 2, 1994, corresponds to FAA 
AD 95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), 
which superseded FAA AD 85-07-04, Amendment 39-5027 (49 FR 45755, 
April 2, 1985).]
    For A300 aeroplanes, and in the frame of the Extended Service 
Goal (ESG) exercise, it was shown that design changes (Airbus Mod. 
4740/Airbus SB A300-57-0128 or Airbus Mod. 5815/Airbus SB A300-57-
0141) were not sufficient to enable full ESG life without 
inspections.
    For A300-600 aeroplanes, since DGAC France AD 1986-187-076(B) 
was issued, a fleet survey and updated Fatigue and Damage Tolerance 
analyses have been performed in order to substantiate the second 
A300-600 ESG2 exercise. Airbus SB A300-57-6005 has been revised 
accordingly to decrease the inspection thresholds and intervals.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 1986-187-076(B)R4, which is 
superseded, and requires those inspections to be accomplished at 
reduced thresholds and intervals.
    This [EASA] AD has been revised to correct typographical errors 
in some compliance times defined in Appendix 1, Tables 1 and 2.

    The MCAI also reduces the number of airplanes identified in the 
applicability by exempting certain Model A300-600 airplanes on which 
certain Airbus modifications have been embodied. 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-2015-8470.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletins A300-57-0116, Revision 07, 
dated September 19, 2011; and A300-57-6005, Revision 06, dated November 
14, 2013. This service information describes procedures for ultrasonic 
inspections of the number 2 flap beam base and side members. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI. 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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Although the MCAI or service information allows further flight 
after cracks are found during compliance with the required action, 
paragraph (m) of this proposed AD requires that you replace the flap 
beam before further flight.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness

[[Page 3047]]

Directive Implementation Aviation Rulemaking Committee (ARC), to 
enhance the AD system. One enhancement was a new process for annotating 
which procedures and tests in the service information are required for 
compliance with an AD. Differentiating these procedures and tests from 
other tasks in the service information is expected to improve an 
owner's/operator's understanding of crucial AD requirements and help 
provide consistent judgment in AD compliance. The procedures and tests 
identified as Required for Compliance (RC) in any service information 
have a direct effect on detecting, preventing, resolving, or 
eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and tests that are not identified as 
RC are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an alternative method of compliance (AMOC), provided the 
procedures and tests identified as RC can be done and the airplane can 
be put back in an airworthy condition. Any substitutions or changes to 
procedures or tests identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 49 airplanes of U.S. 
registry.
    The actions that are required by AD 95-21-09, Amendment 39-9395 (60 
FR 53847, October 18, 1995), and retained in this proposed AD take 
about 6 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 were required by AD 95-
21-09 is $510 per product, per inspection cycle.
    We also estimate that it would take about 6 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $24,990 per 
inspection cycle, or $510 per product, per inspection cycle.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), and adding 
the following new AD:

Airbus: Docket No. FAA-2015-8470; Directorate Identifier 2013-NM-
199-AD.

(a) Comments Due Date

    We must receive comments by March 7, 2016.

(b) Affected ADs

    This AD replaces AD 95-21-09, Amendment 39-9395 (60 FR 53847, 
October 18, 1995).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category.
    (1) Model Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, 
B4-103, and B4-203 airplanes, all manufacturer serial numbers 
(MSNs).
    (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
and B4-622R airplanes, all MSNs.
    (3) Airbus Model A300 F4-605R, all MSNs, except those airplanes 
on which both Airbus Modifications 11133 and 12699 have been 
embodied.
    (4) Airbus Model A300 F4-622R airplanes, all MSNs, except those 
airplanes on which all Airbus Modifications 11133, 12047, 12048, and 
12050 have been embodied, and except those airplanes on which both 
Airbus Modifications 11133 and 12699 have been embodied.
    (5) Airbus Model A300 C4-605R Variant F airplanes, all MSNs.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that the compliance 
times must be reduced. We are issuing this AD to detect and correct 
cracking of the No. 2 flap beams, which could result in rupture of 
the flap beams and reduced structural integrity of the airplane.

(f) Compliance

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

(g) Retained Inspection and Corrective Actions for Model A300 Series 
Airplanes, With Note 3 of AD 95-21-09, Amendment 39-9395 (60 FR 53847, 
October 18, 1995), Incorporated and Additional Terminating Provisions

    This paragraph restates the requirements of paragraph (a) of AD 
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with 
Note 3 of AD 95-21-09 incorporated and additional terminating 
provisions. For Model A300 series airplanes: Prior to the 
accumulation of 15,000 total landings, or within the next 120 days 
after May 9, 1985 (the effective date of AD 85-07-04, Amendment 39-
5027 (49 FR 45755, April 2,

[[Page 3048]]

1985)), whichever occurs later, inspect for cracking of the base 
steel member and light alloy side members of the No. 2 flap beams, 
left hand and right hand, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-116, Revision 6, 
dated July 16, 1993. Accomplishing the requirements of paragraph (h) 
or (l) of this AD terminates the requirements of this paragraph. 
Measurement of crack length is performed by measurement of the probe 
displacement (perpendicular to symmetry plane of beam) between 
defect indication appearance and its complete disappearance. The 
bolt hole indication should not be interpreted as an indication of a 
defect. These two indications appear very close together because the 
defects originate from the bolt holes.
    (1) If no cracking is detected: Except as provided by paragraph 
(i) of this AD, repeat the inspection at intervals not to exceed 
1,700 landings until the requirements of paragraph (h) or (l) of 
this AD are accomplished.
    (2) If any crack is detected that is less than or equal to 4 mm: 
Repeat the inspection at intervals not to exceed 250 landings, until 
the requirements of paragraph (h) or (l) of this AD are 
accomplished.
    (3) If any crack is detected that exceeds 4 mm: Prior to further 
flight, replace the flap beam in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-116, Revision 6, 
dated July 16, 1993, and prior to the accumulation of 15,000 flight 
cycles on the replaced flap beam, perform the ultrasonic inspection 
as required by paragraph (h) or (l) of this AD.

(h) Retained Ultrasonic Inspection and Corrective Action for Model A300 
Series Airplanes, With Additional Terminating Provisions

    This paragraph restates the requirements of paragraph (b) of AD 
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with 
additional terminating provisions. For Model A300 series airplanes: 
Prior to the accumulation of 15,000 total landings, or within the 
next 1,000 landings after November 17, 1995 (the effective date of 
AD 95-21-09), whichever occurs later, perform an ultrasonic 
inspection to detect cracking of the No. 2 flap beams, in accordance 
with Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 
1993. Accomplishment of this inspection terminates the inspections 
required by paragraph (g) of this AD. Accomplishment of the 
requirements of paragraph (l) of this AD terminates the requirements 
of this paragraph.
    (1) If no cracking is detected: Except as provided by paragraph 
(i) of this AD, repeat the ultrasonic inspections thereafter at 
intervals not to exceed 1,700 landings.
    (2) If any crack is detected beyond the bolt hole, and that 
crack is less than or equal to 4 mm in length: Repeat the ultrasonic 
inspections thereafter at intervals not to exceed 250 landings.
    (3) If any crack is detected beyond the bolt hole and that crack 
is greater than 4 mm in length: Prior to further flight, replace the 
flap beam in accordance with Airbus Service Bulletin A300-57-116, 
Revision 6, dated July 16, 1993, and prior to the accumulation of 
15,000 flight cycles on the replaced flap beam, perform the 
ultrasonic inspection as required by this paragraph.

(i) Retained Modification of the No. 2 Track Beam for Model A300 Series 
Airplanes, With Changes to Compliance Extension

    This paragraph restates the provisions of paragraph (c) of AD 
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with 
changes to compliance extension. For Model A300 series airplanes: 
After accomplishing the initial inspection required by paragraph (h) 
of this AD, accomplishment of either paragraph (i)(1) or (i)(2) of 
this AD before the effective date of this AD extends the fatigue 
life of the No. 2 flap track beam as specified in those paragraphs, 
provided that no cracking is detected during any inspection required 
by paragraph (g) or (h) of this AD.
    (1) Removal of any damage and the installation of larger 
diameter bolts on the No. 2 flap track beam (Modification No. 4740), 
in accordance with Airbus Service Bulletin A300-57-128, Revision 3, 
dated January 26, 1990, extends the interval for the first 
repetitive inspection required by paragraph (h) of this AD from 
1,700 landings to 12,000 landings, provided that Modification No. 
4740 is accomplished prior to the accumulation of 16,700 total 
landings on the flap beams. Following accomplishment of the first 
repetitive inspection, subsequent repetitive inspections shall be 
performed at intervals not to exceed 1,700 landings. Or
    (2) Cold working of the bolt holes and the installation of 
larger diameter bolts on the No. 2 flap track beam (Modification No. 
5815), in accordance with Airbus Service Bulletin A300-57-141, 
Revision 7, dated July 16, 1993, extends the interval for the first 
repetitive inspection required by paragraph (h) of this AD from 
1,700 landings to the interval specified in paragraph (i)(2)(i) or 
(i)(2)(ii) of this AD.
    (i) If interference fit bolts that are 15/32-inch in diameter 
are fitted, the interval for the first repetitive inspection 
required by paragraph (h) of this AD is extended to 22,000 landings, 
provided that Modification 5815 is accomplished prior to the 
accumulation of 16,700 total landings on the flap beam. Following 
accomplishment of the first repetitive inspection required by 
paragraph (h) of this AD, subsequent repetitive inspections shall be 
performed at intervals not to exceed 1,700 landings. Or
    (ii) If interference fit bolts that are 7/16- or 3/8-inch in 
diameter are fitted, the interval for the first repetitive 
inspection required by paragraph (h) of this AD is extended to 
33,000 landings, provided that Modification 5815 is accomplished 
prior to the accumulation of 16,700 total landings on the flap beam. 
Following accomplishment of the first repetitive inspection required 
by paragraph (h) of this AD, subsequent repetitive inspections shall 
be performed at intervals not to exceed 1,700 landings.

(j) Retained Ultrasonic Inspection and Corrective Actions for Model 
A300-600 Series Airplanes, With Terminating Provisions

    This paragraph restates the requirements of paragraph (d) of AD 
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with 
terminating provisions. For Model A300-600 series airplanes: Prior 
to the accumulation of 15,000 total landings, or within the next 
1,000 landings after November 17, 1995 (the effective date of AD 95-
21-09), whichever occurs later, perform an ultrasonic inspection to 
detect cracking of the No. 2 flap track beams, in accordance with 
Airbus Service Bulletin A300-57-6005, Revision 2, dated December 16, 
1993. Accomplishing the actions required by paragraph (l) of this AD 
terminates the requirements of this paragraph.
    (1) If no cracking is detected, repeat the ultrasonic 
inspections thereafter at intervals not to exceed 1,700 landings.
    (2) If any crack is detected beyond the bolt hole and that crack 
is less than or equal to 4 mm in length: Repeat the ultrasonic 
inspections thereafter at intervals not to exceed 250 landings.
    (3) If any crack is detected beyond the bolt hole and that crack 
is greater than 4 mm in length: Prior to further flight, replace the 
flap beam in accordance with Airbus Service Bulletin A300-57-6005, 
Revision 2, dated December 16, 1993, and prior to the accumulation 
of 15,000 landings on the replaced flap beam, perform the ultrasonic 
inspection required by paragraph (j) of this AD.

(k) Retained Optional Action With Note 5 of AD 95-21-09 Amendment 39-
9395 (60 FR 53847, October 18, 1995), Incorporated and Changes to 
Terminating Action

    This paragraph restates the provisions of paragraph (e) of AD 
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), with 
Note 5 of AD 95-21-09 incorporated and changes to terminating 
action. For Model A300-600 series airplanes: Installation of 
oversized transition fit bolts in cold-worked holes, in accordance 
with Airbus Service Bulletin A300-57-6006 (Modification 5815), 
Revision 4, dated July 25, 1994, constitutes terminating action for 
the repetitive inspection requirements of paragraph (j) of this AD, 
provided that no cracking is detected during any inspection required 
by paragraph (j) of this AD, and provided that the installation is 
accomplished prior to the accumulation of 15,000 total landings and 
before the effective date of this AD. If any bolt requires 
oversizing above 7/16-inch diameter during accomplishment of this 
installation, prior to further flight, repair using a method 
approved by the Manager, Standardization Branch, ANM-113, FAA, 
Transport Airplane Directorate, or by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA. As of the 
effective date of this AD, any new repair approval must be done 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA. If Airbus Service Bulletin 
A300-57-6005, Revision 2, dated December 16, 1993, is accomplished 
concurrently with

[[Page 3049]]

Airbus Service Bulletin A300-57-6006, Revision 3, dated December 16, 
1993 (Modification 5815), the ultrasonic inspection for cracking 
required by paragraph (j) of this AD need not be performed since the 
eddy current inspection detailed for Modification 5815 is more 
comprehensive.

(l) New Requirement of This AD: Initial and Repetitive Ultrasonic 
Inspections

    At the applicable time specified in paragraph (l)(1) or (l)(2) 
of this AD and, thereafter at intervals not to exceed those defined 
in table 3 to paragraph (l) of this AD, as applicable, accomplish an 
ultrasonic inspection for cracking of the steel base member and the 
aluminum side members' flap beam on the left-hand (LH) and right-
hand (RH) sides in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-57-0116, Revision 07, dated 
September 19, 2011, including Appendixes A and B, undated; or Airbus 
Service Bulletin A300-57-6005, Revision 06, dated November 14, 2013; 
as applicable. For the purposes of this AD, average flight time 
(AFT) is considered to be the number of flight hours per flight 
cycle. Doing the actions required by this paragraph terminates the 
requirements of paragraphs (g) through (k) of this AD.
    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes (referred to as Model A300 series airplanes): 
Within the applicable compliance time defined in table 1 to 
paragraph (l) of this AD.
    (2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, F4-622R airplanes, and Model A300 C4-605R 
Variant F airplanes (referred to as Model A300-600 series 
airplanes): At the later of the times specified in paragraphs 
(l)(2)(i) and (l)(2)(ii) of this AD.
    (i) Within the compliance time defined in table 2 to paragraph 
(l) of this AD.
    (ii) Within 300 flight cycles or 640 flight hours after the 
effective date of this AD, whichever occurs first.

  Table 1 to Paragraph (l) of This AD--Inspection Compliance Times for
                       Model A300 Series Airplanes
------------------------------------------------------------------------
                                                       Compliance times
                                   Compliance times   for airplanes with
     Airplane configuration       for airplanes with    an AFT of more
                                    an AFT of less     than or equal to
                                       than 1.5               1.5
------------------------------------------------------------------------
Model A300 B2-1A, B2-1C, B2K-3C,  Within 15,000       Within 15,000
 B2-203 airplanes on which         flight cycles or    flight cycles or
 Airbus Modifications 4740 and     16,900 flight       16,900 flight
 5815 have not been embodied.      hours since first   hours since first
                                   flight of the       flight of the
                                   airplane,           airplane,
                                   whichever occurs    whichever occurs
                                   first.              first.
Model A300 B4-103 airplanes on    Within 15,000       Within 15,000
 which Airbus Modifications 4740   flight cycles or    flight cycles or
 and 5815 have not been embodied.  20,500 flight       20,500 flight
                                   hours since first   hours since first
                                   flight of the       flight of the
                                   airplane,           airplane,
                                   whichever occurs    whichever occurs
                                   first.              first.
Model A300 B4-2C, and B4-203      Within 16,200       Within 15,000
 airplanes on which Airbus         flight cycles or    flight cycles or
 Modifications 4740 and 5815       22,200 flight       34,000 flight
 have not been embodied.           hours since first   hours since first
                                   flight of the       flight of the
                                   airplane,           airplane,
                                   whichever occurs    whichever occurs
                                   first.              first.
Model A300 B2-1A, B2-1C, B2K-3C,  Within 12,000       Within 12,000
 B2-203 airplanes on which         flight cycles or    flight cycles or
 Airbus Modification 4740 has      13,500 flight       13,500 flight
 been embodied.                    hours since         hours since
                                   embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   4740, whichever     4740, whichever
                                   occurs first.       occurs first.
Model A300 B4-103 airplanes on    Within 12,000       Within 12,000
 which Airbus Modification 4740    flight cycles or    flight cycles or
 has been embodied.                16,400 flight       16,400 flight
                                   hours since         hours since
                                   embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   4740, whichever     4740, whichever
                                   occurs first.       occurs first.
Model A300 B4-2C, and B4-203      Within 12,900       Within 12,000
 airplanes on which Airbus         flight cycles or    flight cycles or
 Modification 4740 has been        17,700 flight       27,200 flight
 embodied.                         hours since         hours since
                                   embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   4740, whichever     4740, whichever
                                   occurs first.       occurs first.
Model A300 B2-1A, B2-1C, B2K-3C,  Within 33,000       Within 33,000
 B2-203 airplanes on which         flight cycles or    flight cycles or
 Airbus Modification 5815 has      37,200 flight       37,200 flight
 been embodied and no bolt         hours since         hours since
 larger than 7/16-inch diameter    embodiment of       embodiment of
 is fitted.                        Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B4-103 airplanes on    Within 33,000       Within 33,000
 which Airbus Modification 5815    flight cycles or    flight cycles or
 has been embodied and no bolt     45,200 flight       45,200 flight
 larger than 7/16-inch diameter    hours since         hours since
 is fitted.                        embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B4-2C, and B4-203      Within 35,600       Within 33,000
 airplanes on which Airbus         flight cycles or    flight cycles or
 Modification 5815 has been        48,800 flight       74,900 flight
 embodied and no bolt larger       hours since         hours since
 than 7/16-inch diameter is        embodiment of       embodiment of
 fitted.                           Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B2-1A, B2-1C, B2K-3C,  Within 22,000       Within 22,000
 B2-203 airplanes on which         flight cycles or    flight cycles or
 Airbus Modification 5815 has      24,800 flight       24,800 flight
 been embodied and at least one    hours since         hours since
 bolt with a 15/32[dash]inch       embodiment of       embodiment of
 diameter is fitted.               Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B4-103 airplanes on    Within 22,000       Within 22,000
 which Airbus Modification 5815    flight cycles or    flight cycles or
 has been embodied and at least    30,100 flight       30,100 flight
 one bolt with a 15/32[dash]inch   hours since         hours since
 diameter is fitted.               embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300 B4-2C, and B4-203,     Within 23,700       Within 22,000
 airplanes on which Airbus         flight cycles or    flight cycles or
 Modification 5815 has been        32,500 flight       49,900 flight
 embodied and at least one bolt    hours since         hours since
 with a 15/32-inch diameter is     embodiment of       embodiment of
 fitted.                           Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
------------------------------------------------------------------------


Table 2 to Paragraph (l) of This AD--Compliance Times for Model A300-600
                            Series Airplanes
------------------------------------------------------------------------
                                                       Compliance times
                                   Compliance times   for airplanes with
     Airplane configuration       for airplanes with    an AFT of more
                                    an AFT of less     than or equal to
                                       than 1.5               1.5
------------------------------------------------------------------------
Model A300-600 series airplanes   Within 16,200       Within 15,000
 on which Airbus Modification      flight cycles or    flight cycles or
 5815 and Airbus Modification      24,300 flight       32,400 flight
 11133 have not been embodied.     hours since first   hours since first
                                   flight of the       flight of the
                                   airplane,           airplane,
                                   whichever occurs    whichever occurs
                                   first.              first.

[[Page 3050]]

 
Model A300-600 series airplanes   Within 35,600       Within 33,000
 on which Airbus Modification      flight cycles or    flight cycles or
 5815 has been embodied and no     53,400 flight       71,200 flight
 bolt larger than 7/16-inch        hours since         hours since
 diameter is fitted.               embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300-600 series airplanes   Within 23,700       Within 22,000
 on which Airbus Modification      flight cycles or    flight cycles or
 5815 has been embodied and at     35,600 flight       47,500 flight
 least one bolt 15/32-inch         hours since         hours since
 diameter is fitted.               embodiment of       embodiment of
                                   Airbus              Airbus
                                   Modification        Modification
                                   5815, whichever     5815, whichever
                                   occurs first.       occurs first.
Model A300-600 series airplanes   Within 35,600       Within 33,000
 on which Airbus Modification      flight cycles or    flight cycles or
 11133 has been embodied.          53,400 flight       71,200 flight
                                   hours since first   hours since first
                                   flight, whichever   flight, whichever
                                   occurs first.       occurs first.
------------------------------------------------------------------------


  Table 3 to Paragraph (l) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
                                      Repetitive          Repetitive
                                   interval (not to    interval (not to
                                      exceed) for         exceed) for
         Airplane models           airplanes with an   airplanes with an
                                   AFT of less than     AFT equal to or
                                          1.5            more than 1.5
------------------------------------------------------------------------
A300 B2-1A, B2-1C, B2K-3C, B2-    1,500 flight        1,500 flight
 203.                              cycles or 1,600     cycles or 1,600
                                   flight hours,       flight hours,
                                   whichever occurs    whichever occurs
                                   first.              first.
A300B4-103 airplanes............  1,500 flight        1,500 flight
                                   cycles or 2,000     cycles or 2,000
                                   flight hours,       flight hours,
                                   whichever occurs    whichever occurs
                                   first.              first.
A300 B4-2C, and B4-203..........  1,600 flight        1,500 flight
                                   cycles or 2,200     cycles or 3,400
                                   flight hours,       flight hours,
                                   whichever occurs    whichever occurs
                                   first.              first.
A300-600 series airplanes.......  1,600 flight        1,500 flight
                                   cycles or 2,400     cycles or 3,200
                                   flight hours,       flight hours,
                                   whichever occurs    whichever occurs
                                   first.              first.
------------------------------------------------------------------------

(m) New Requirement of This AD: Corrective Action

    If any crack is found during any inspection required by 
paragraph (l) of this AD: Before further flight, replace the flap 
beam using a method approved by 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). Replacement of the flap beam does not constitute 
terminating action for the inspections required by paragraph (l) of 
this AD.

(n) Credit for Previous Actions

    (1) This paragraph provides credit for inspections required by 
paragraph (g) of this AD, if those inspections were performed before 
November 17, 1995 (the effective date of AD 95-21-09, Amendment 39-
9395 (60 FR 53847, October 18, 1995)) using Airbus Service Bulletin 
A300-57-116, Revision 1, dated August 27, 1983; Revision 2, dated 
April 24, 1984; Revision 3, dated July 20, 1984; Revision 4, dated 
August 13, 1986; or Revision 5, dated July 10, 1989; as applicable.
    (2) This paragraph provides credit for actions required by 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
identified in paragraphs (n)(2)(i) through (n)(2)(x) of this AD.
    (i) Airbus Service Bulletin A300-57-6005, Revision 03, dated 
November 25, 1997, which was not previously incorporated by 
reference.
    (ii) Airbus Service Bulletin A300-57-6005, Revision 04, dated 
October 25, 1999, which was not previously incorporated by 
reference.
    (iii) Airbus Service Bulletin A300-57-6005, Revision 05, dated 
April 25, 2013, which was not previously incorporated by reference.
    (iv) Airbus Service Bulletin A300-57-6005, Revision 2, dated 
December 16, 1993, which was previously incorporated by reference on 
November 17 1995 (60 FR 53847, October 18, 1995).
    (v) Airbus Service Bulletin A300-57-116, Revision 1, dated 
August 27, 1983, which was not previously incorporated by reference.
    (vi) Airbus Service Bulletin A300-57-116, Revision 2, dated 
April 24, 1984, which was not previously incorporated by reference.
    (vii) Airbus Service Bulletin A300-57-116, Revision 3, dated 
July 20, 1984, which was not previously incorporated by reference.
    (viii) Airbus Service Bulletin A300-57-116, Revision 4, dated 
August 13, 1986, which was not previously incorporated by reference.
    (ix) Airbus Service Bulletin A300-57-116, Revision 5, dated July 
10, 1989, which was not previously incorporated by reference.
    (x) Airbus Service Bulletin A300-57-116, Revision 6, dated July 
16, 1993, which was previously incorporated by reference on November 
17, 1995 (60 FR 53847, October 18, 1995).

(o) 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 95-21-09, Amendment 39-
9395 (60 FR 53847, October 18, 1995), are approved as AMOCs for the 
corresponding provisions of paragraphs (g) through (j) 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.
    (3) Required for Compliance (RC): Except as required by 
paragraph (m) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without

[[Page 3051]]

obtaining approval of an AMOC, provided the procedures and tests 
identified as RC can be done and the airplane can be put back in an 
airworthy condition. Any substitutions or changes to procedures or 
tests identified as RC require approval of an AMOC.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2013-0234R2, dated October 7, 2013, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2015-8470.
    (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 6. 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-00634 Filed 1-19-16; 8:45 am]
BILLING CODE 4910-13-P


