81 FR 65860 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 186 (September 26, 2016)

We are superseding Airworthiness Directive (AD) 2000-10-18 for certain Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2000-10-18 required repetitive inspections to detect cracks in the lower spar of the engine pylons between ribs 6 and 7, and repair if necessary. This new AD reduces the compliance times for the initial inspection and the repetitive intervals. This AD was prompted by the determination that the compliance times for the initial inspection and the repetitive intervals must be reduced to allow timely detection of cracks in the engine pylon's lower spar between ribs 6 and 7. We are issuing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the engine pylon's lower spar, and possible separation of the engine from the airplane.

[Federal Register Volume 81, Number 186 (Monday, September 26, 2016)]
[Rules and Regulations]
[Pages 65860-65864]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-22460]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5039; Directorate Identifier 2013-NM-148-AD; 
Amendment 39-18659; AD 2016-19-10]
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) 2000-10-18 for 
certain Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, 
F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes); and Model A310 
series airplanes. AD 2000-10-18 required repetitive inspections to 
detect cracks in the lower spar of the engine pylons between ribs 6 and 
7, and repair if necessary. This new AD reduces the compliance times 
for the initial inspection and the repetitive intervals. This AD was 
prompted by the determination that the compliance times for the initial 
inspection and the repetitive intervals must be reduced to allow timely 
detection of cracks in the engine pylon's lower spar between ribs 6 and 
7. We are issuing this AD to detect and correct fatigue cracking, which 
could result in reduced structural integrity of the engine pylon's 
lower spar, and possible separation of the engine from the airplane.

DATES: This AD is effective October 31, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 31, 
2016.

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 [email protected]; 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-2016-
5039.

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-
5039; 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 2000-10-18, Amendment 39-11742 (65 FR 34055, 
May 26, 2000) (``AD 2000-10-18''). AD 2000-10-18 applied to certain 
Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, F4-600R 
series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes); and Model A310 
series airplanes. The NPRM published in the Federal Register on April 
5, 2016 (81 FR 19505) (``the NPRM''). The NPRM was prompted by a 
determination that the compliance times for the initial inspection and 
the repetitive intervals must be reduced to allow timely detection of 
cracks in the engine pylon's lower spar between ribs 6 and 7. The NPRM 
proposed to continue to require repetitive inspections to detect cracks 
in the lower spar of the engine pylons between ribs 6 and 7, and repair 
if necessary. The NPRM also proposed to reduce the compliance times for 
the initial inspection and the repetitive intervals. We are issuing 
this AD to detect and correct fatigue cracking, which could result in 
reduced structural integrity of the engine pylon's lower spar, and 
possible separation of the engine from the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent

[[Page 65861]]

for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0167, dated July 26, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition. The MCAI states:

    Cracks were found between ribs 6 and 7 in the lower spar of 
engine pylons on A310, A300 and A300-600 aeroplanes. To prevent 
crack initiation, a first inspection programme of this area was 
rendered mandatory by DGAC [Direction G[eacute]n[eacute]rale de 
l'Aviation Civile] France AD 93-228-154 (later revised, currently at 
Revision 3) [which corresponds to certain actions in FAA AD 2000-10-
18] for A300 and A300-600 aeroplanes.
    At a later date and due to new findings, a specific inspection 
programme for A310 aeroplanes was rendered mandatory by DGAC France 
AD 1999-239-287(B) [which corresponds to certain other actions in 
FAA AD 2000-10-18]. That [French] AD was later superseded by EASA AD 
2008-0001, which introduced new thresholds and intervals in the 
frame of the A310 extended service goal (ESG) exercise.
    Since DGAC France AD 1993-228-154(B)R3 and EASA AD 2008-0001 
were issued, a fleet survey and updated Fatigue and Damage Tolerance 
analyses have been performed in order to substantiate the second ESG 
for A300-600, called ESG2 exercise. The results of these analyses 
have shown that the inspection threshold and interval must be 
reduced to allow timely detection of cracks in the engine pylon 
lower spar between ribs 6 and 7.
    For the reasons described above, this new [EASA] AD retains the 
requirements of DGAC France AD 1993-228-154(B)R3 and EASA AD 2008-
0001, which are superseded, and requires accomplishment of the [eddy 
current or liquid penetrant] inspections [for cracking] and, 
depending on findings, [related investigative and] corrective 
actions [repairs], within the new thresholds and intervals specified 
in Airbus Service Bulletin (SB) A300-54-0073 Revision 03 [dated 
October 11, 2012] or SB A310-54-2017 Revision 06 [dated October 3, 
2012] or SB A300-54-6014 Revision 07 [dated September 5, 2012].

    Related investigative actions include eddy current or liquid 
penetrant inspections for cracking of areas with removed protection. 
The unsafe condition is cracking in the lower spar of the engine pylons 
between ribs 6 and 7, which could result in reduced structural 
integrity of the engine pylon's lower spar, and possible separation of 
the engine from the airplane. You may examine the MCAI in the AD docket 
on the Internet at http://www.regulations.gov by searching for and 
locating it in Docket No. FAA-2016-5039.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Revise Applicability

    United Parcel Service (UPS) requested that we remove Model A300 F4-
622R airplanes from the proposed applicability. UPS stated that the 
NPRM would apply to all Model A300 airplanes except those that have 
Airbus Modification 10599 incorporated in production. UPS explained 
that Airbus Modification 10559 was embodied on airplane manufacturer 
serial number (MSN) 723 and all subsequent airplane serial numbers; and 
that the first Model A300 F4-622R airplane with this modification 
embodied was MSN 805.
    We infer that UPS made a typographical error in citing the Airbus 
Modification number and intended to reference Airbus Modification 
10149. We agree with the commenter's request to remove Model A300 F4-
622R airplanes from the applicability. Airbus has verified that all 
Model A300 F4-622R airplanes are post-Airbus Modification 10149 and 
that operators do not need to accomplish the inspections specified in 
Airbus Service Bulletin A300-54-6014, Revision 07, dated September 5, 
2012, on those airplanes. As specified in paragraph (c) of this AD, 
this AD does not affect airplanes on which Airbus Modification 10149 
has been incorporated in production. We have removed Model A300 F4-622R 
airplanes from paragraph (c)(4) of this AD. This change has been 
coordinated with EASA.

Requests To Revise Paragraphs (g), (h), and (i) of the Proposed AD

    UPS requested that we revise paragraphs (g), (h), and (i) of the 
proposed AD, which identify inspections, corrective actions, and 
exceptions for both pre-repair and post-repair modification 
configurations. UPS stated that these paragraphs contain information in 
long, complex sentences with cross references to other paragraphs in 
the proposed AD. UPS explained that there is potential for confusion of 
the ruling requirements and opportunities for compliance errors. UPS 
provided suggestions for revising certain paragraphs of the proposed 
AD.
    We do not agree with the commenter's request. We recognize that the 
actions specified in the service information and this AD are complex. 
However, this AD uses standard terminology that is legally enforceable. 
UPS's suggested revisions included doing all repairs using a method 
approved by the FAA, EASA, or Airbus's EASA Design Organization 
Approval. This suggestion would require operators to obtain a method of 
compliance, even though the service information does provide 
instructions for doing certain repairs. Also, UPS suggested we add 
regulatory material in a note, which is not legally enforceable. We 
have not changed this AD in this regard.

Request To Define Average Flight Time (AFT) Calculations

    UPS requested that we include a paragraph to define how AFT is 
calculated. UPS explained that paragraph (g) of the proposed AD has 
repetitive inspection requirements that use an interval defined in the 
service information that is dependent on airplane AFT methodology, but 
that the NPRM does not define parameters for how and when the AFT is 
determined. UPS submitted proposed language for calculating AFTs.
    In regards to the AFT definition, we have determined that, for the 
reasons stated by the commenter, this AD should define AFT 
calculations. We have added paragraph (j) to this AD accordingly and 
redesignated subsequent paragraphs.

Request To Approve Alternative Methods of Compliance (AMOCs)

    UPS requested that we revise paragraph (k) of the proposed AD to 
specify that AMOCs approved previously for AD 2000-10-18 are approved 
as AMOCs for the corresponding provisions of this AD.
    We agree with the commenter's request. We have revised paragraph 
(l) of this AD (referred to as paragraph (k) in the proposed AD) to 
specify that AMOCs approved previously for AD 2000-10-18 are approved 
as AMOCs for the corresponding provisions of this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these 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

    Airbus has issued the following service bulletins.
     Airbus Service Bulletin A300-54-0073, Revision 03, dated 
October 11, 2012 (for Model A300 series airplanes).

[[Page 65862]]

     Airbus Service Bulletin A300-54-6014, Revision 07, dated 
September 5, 2012 (for Model A300-600 series airplanes).
     Airbus Service Bulletin A310-54-2017, Revision 06, dated 
October 3, 2012 (for Model A310 series airplanes).
    This service information describes procedures for inspecting for 
cracking of the engine pylon's lower spar between ribs 6 and 7, and 
related investigative actions if cracking is found. 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 156 airplanes of U.S. registry.
    We also estimate that it would take about 6 work-hours per product 
to comply with the 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 $79,560, or $510 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD. We 
have no way of determining the number of aircraft that might need these 
actions.

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) 
2000-10-18, Amendment 39-11742 (65 FR 34055, May 26, 2000), and adding 
the following new AD:

2016-19-10 Airbus: Amendment 39-18659; Docket No. FAA-2016-5039; 
Directorate Identifier 2013-NM-148-AD.

(a) Effective Date

    This AD is effective October 31, 2016.

(b) Affected ADs

    This AD replaces AD 2000-10-18, Amendment 39-11742 (65 FR 34055, 
May 26, 2000) (``AD 2000-10-18'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(6) of this AD, certificated in any category, 
except airplanes on which Airbus Modification 10149 has been 
incorporated in production.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (3) Airbus Model A300 B4-605R and B4-622R airplanes.
    (4) Airbus Model A300 F4-605R airplanes.
    (5) Airbus Model A300 C4-605R Variant F airplanes.
    (6) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Reason

    This AD was prompted by the determination that the compliance 
times for the initial inspection and the repetitive intervals must 
be reduced to allow timely detection of cracks in the engine pylon's 
lower spar between ribs 6 and 7. We are issuing this AD to detect 
and correct fatigue cracking, which could result in reduced 
structural integrity of the engine pylon's lower spar, and possible 
separation of the engine from the airplane.

(f) Compliance

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

(g) Inspections and Corrective Actions

    Except as provided by paragraphs (i)(1) and (i)(2) of this AD, 
at the applicable time specified in paragraph 1.E., ``Compliance,'' 
of the applicable Airbus service bulletin specified in paragraph 
(g)(1), (g)(2), or (g)(3) of this AD: Do an eddy current or liquid 
penetrant inspection for cracking of the engine pylon's lower spar 
between ribs 6 and 7; and do all applicable related investigative 
and corrective actions; in accordance with the Accomplishment 
Instructions of the applicable Airbus service bulletin specified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD, except as required 
by paragraph (i)(3) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspection of the engine pylon's lower spar between ribs 6 and 7 
thereafter at the applicable time and intervals specified in 
paragraph 1.E., ``Compliance,'' of the applicable Airbus service 
bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD 
until a repair or modification specified in the Accomplishment 
Instructions of the applicable Airbus service bulletin identified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD is done.
    (1) Airbus Service Bulletin A300-54-0073, Revision 03, dated 
October 11, 2012 (for Model A300 series airplanes).

    Note 1 to paragraph (g)(1) of this AD: Airbus Service Bulletin 
A300-54-0080, Revision 02, dated July 9, 2002, is an additional 
source of guidance for accomplishing the modification specified in 
Airbus Service Bulletin A300-54-0073, Revision 03, dated October 11, 
2012.

    (2) Airbus Service Bulletin A300-54-6014, Revision 07, dated 
September 5, 2012 (for Model A300-600 series airplanes).

    Note 2 to paragraph (g)(2) of this AD: Airbus Service Bulletin 
A300-54-6020, Revision 02, dated July 9, 2002, is an additional 
source of guidance for accomplishing the modification specified in 
Airbus Service Bulletin A300-54-6014, Revision 07, dated September 
5, 2012.

    (3) Airbus Service Bulletin A310-54-2017, Revision 06, dated 
October 3, 2012 (for Model A310 series airplanes).

    Note 3 to paragraph (g)(3) of this AD: Airbus Service Bulletin 
A310-54-2023,

[[Page 65863]]

Revision 03, dated July 9, 2002, is an additional source of guidance 
for accomplishing the modification specified in Airbus Service 
Bulletin A310-54-2017, Revision 06, dated October 3, 2012.

(h) Post-Repair/Modification and Corrective Actions

    For airplanes on which any repair or modification specified in 
the Accomplishment Instructions of the applicable Airbus service 
bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this 
AD is done: Except as provided by paragraphs (i)(1) and (i)(2) of 
this AD, at the applicable time specified in paragraph 1.E., 
``Compliance,'' of the applicable Airbus service bulletin specified 
in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do an eddy 
current or liquid penetrant inspection for cracking of the engine 
pylon's lower spar between ribs 6 and 7; and do all applicable 
related investigative and corrective actions; in accordance with the 
Accomplishment Instructions of the applicable Airbus service 
bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this 
AD, except as required by paragraph (i)(3) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight. Repeat the inspection of the engine pylon's lower 
spar between ribs 6 and 7 thereafter at the applicable time and 
intervals specified in paragraph 1.E., ``Compliance,'' of the 
applicable Airbus service bulletin specified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD.

(i) Exceptions to Service Information

    (1) Where a ``Threshold'' is specified in paragraph 1.E., 
``Compliance,'' of the service information specified in paragraphs 
(g)(1), (g)(2), and (g)(3) of this AD, the ``FC'' and ``FH'' 
compliance times are total flight cycle and total flight hour 
compliance times, except that if a repair or service bulletin 
identified in paragraph 1.E., ``Compliance,'' of the service 
bulletins specified in paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD has been done, the ``FC'' and ``FH'' compliance times are flight 
cycle and flight hour compliance times since the identified repair 
or service bulletin was done.
    (2) Except as provided by paragraphs (i)(2)(i) and (i)(2)(ii) of 
this AD: For the ``Grace period'' specified in paragraph 1.E., 
``Compliance,'' of the service information specified in paragraphs 
(g)(1), (g)(2), and (g)(3) of this AD, operators must comply with 
the actions specified in paragraphs (g) and (h) of this AD, as 
applicable, at the later of the applicable times in the 
``Threshold'' and ``Grace Period'' times specified in paragraph 
1.E., ``Compliance,'' of the applicable service information, except 
the language ``for aircraft that have already exceeded or are close 
to exceed[ing] the threshold or scheduled interval'' does not apply.
    (i) Where Airbus Service Bulletin A300-54-0073, Revision 03, 
dated October 11, 2012; and Airbus Service Bulletin A310-54-2017, 
Revision 06, dated October 3, 2012; specify a compliance time ``. . 
. after receipt of this Inspection Service Bulletin without 
exceeding the requirements of previous issue of this ISB,'' this AD 
requires compliance within the specified compliance time after the 
effective date of this AD.
    (ii) Where Airbus Service Bulletin A300-54-6014, Revision 07, 
dated September 5, 2012, specifies a compliance time ``. . . after 
receipt of this Inspection Service Bulletin without exceeding the 
requirements of previous issue of this SB,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (3) If any crack is found during any inspection required by this 
AD and the applicable Airbus service bulletin specified in paragraph 
(g)(1), (g)(2), or (g)(3) of this AD specifies to contact Airbus: 
Before further flight, repair the crack 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).

(j) Calculating Average Flight Time (AFT)

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

(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 an applicable service 
bulletin specified in paragraphs (k)(1) through (k)(10) of this AD.
    (1) Airbus Service Bulletin A300-54-0073, Revision 1, dated 
March 28, 1994 (for Model A300 series airplanes), which was 
incorporated by reference in AD 96-11-05, Amendment 39-9630 (61 FR 
26091, May 24, 1996) (``AD 96-11-05'').
    (2) Airbus Service Bulletin A300-54-0073, Revision 02, dated 
July 9, 2002 (for Model A300 series airplanes), which is not 
incorporated by reference in this AD.
    (3) Airbus Service Bulletin A300-54-6014, Revision 1, dated 
March 28, 1994 (for Model A300-600 series airplanes), which was 
incorporated by reference in AD 96-11-05.
    (4) Airbus Service Bulletin A300-54-6014, Revision 03, dated 
June 4, 1998 (for Model A300-600 series airplanes), which is not 
incorporated by reference in this AD.
    (5) Airbus Service Bulletin A300-54-6014, Revision 04, dated 
March 9, 2002 (for Model A300-600 series airplanes), which is not 
incorporated by reference in this AD.
    (6) Airbus Service Bulletin A300-54-6014, Revision 05, dated 
September 1, 2011 (for Model A300-600 series airplanes), which is 
not incorporated by reference in this AD.
    (7) Airbus Service Bulletin A300-54-6014, Revision 06, dated May 
24, 2012 (for Model A300-600 series airplanes), which is not 
incorporated by reference in this AD.
    (8) Airbus Service Bulletin A310-54-2017, Revision 03, dated 
June 11, 1999 (for Model A310 series airplanes), which was 
incorporated by reference in AD 2000-10-18.
    (9) Airbus Service Bulletin A310-54-2017, Revision 04, dated 
July 9, 2002 (for Model A310 series airplanes), which is not 
incorporated by reference in this AD.
    (10) Airbus Service Bulletin A310-54-2017, Revision 05, dated 
November 16, 2007 (for Model A310 series airplanes), which is not 
incorporated by reference 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: [email protected].
    (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 2000-10-18 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 the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0167, dated July 26, 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-2016-5039.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(4) 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.

[[Page 65864]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-54-0073, Revision 03, dated 
October 11, 2012.
    (ii) Airbus Service Bulletin A300-54-6014, Revision 07, dated 
September 5, 2012.
    (iii) Airbus Service Bulletin A310-54-2017, Revision 06, dated 
October 3, 2012.
    (3) 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 [email protected]; 
Internet http://www.airbus.com.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 12, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-22460 Filed 9-23-16; 8:45 am]
 BILLING CODE 4910-13-P