81 FR 19505 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 65 (April 5, 2016)

Page Range		19505-19509
FR Document		2016-07569
We propose to supersede airworthiness directive (AD) 2000-10- 18, that applies 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. AD 2000-10-18 requires repetitive inspections to detect cracks in the lower spar of the engine pylons between ribs 6 and 7, and repair if necessary. Since we issued AD 2000-10-18, we have determined 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. This proposed AD would reduce the compliance times for the initial inspection and the repetitive intervals. We are proposing this AD to prevent 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 Issue 65 (Tuesday, April 5, 2016)
[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)]
[Proposed Rules]
[Pages 19505-19509]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-07569]


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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]
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) 2000-10-
18, that applies 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. AD 2000-10-18 requires 
repetitive inspections to detect cracks in the lower spar of the engine 
pylons between ribs 6 and 7, and repair if necessary. Since we issued 
AD 2000-10-18, we have determined 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. This proposed AD would reduce the compliance 
times for the initial inspection and the repetitive intervals. We are 
proposing this AD to prevent 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: We must receive comments on this proposed AD by May 20, 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 [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.

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 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-2016-5039; 
Directorate Identifier 2013-NM-148-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://

[[Page 19506]]

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 May 16, 2000, we issued AD 2000-10-18, Amendment 39-11742 (65 FR 
34055, May 26, 2000). AD 2000-10-18 requires actions intended to 
address an unsafe condition on 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.
    Since we issued AD 2000-10-18, Amendment 39-11742 (65 FR 34055, May 
26, 2000), we have determined 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 European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, 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) [http://ad.easa.europa.eu/blob/19932283tb__Superseded.pdf/AD_F-1993-228-154R3_1] [which corresponds 
to certain actions in in FAA AD 2000-10-18, Amendment 39-11742 (65 
FR 34055)] 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, Amendment 39-11742 (65 FR 34055, May 26, 2000)]. 
That [French] AD was later superseded by EASA AD 2008-0001 [http://ad.easa.europa.eu/blob/easa_ad_2008_0001_Superseded.pdf/AD_2008-0001_1], 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.
    The compliance times for the inspections vary, depending on 
airplane configuration and utilization as follows.
    For Model A300-600 series airplanes:
     The compliance time for the initial inspection is before 
the accumulation of 10,900 total flight cycles.
     The compliance times for the repetitive inspection 
interval are 5,700 flight cycles for pre-doubler modified airplanes; 
and for post-doubler modified airplanes, the compliance times range 
from 7,200 flight cycles or 8,200 flight hours, to 8,400 flight cycles 
or 16,000 flight hours.
     The compliance times for the initial inspection following 
crack repair range from 5,200 flight cycles or 5,900 flight hours, to 
6,600 flight cycles or 13,400 flight hours; and the compliance times 
for the post-repair repetitive inspection range from 2,200 flight 
cycles or 2,500 flight hours, to 3,400 flight cycles or 6,900 flight 
hours.
    For Model A300 series airplanes:
     The compliance times for the initial inspection range from 
before the accumulation of 4,400 total flight cycles to 9,400 total 
flight cycles.
     The compliance times for the repetitive inspection 
interval range from 4,400 flight cycles to 6,100 flight cycles.
     The initial inspection compliance times for post-doubler 
modified airplanes range from 12,700 flight cycles or 25,700 flight 
hours, to 20,700 flight cycles or 30,900 flight hours after the 
modification; the post-doubler repetitive inspection interval ranges 
from 7,800 flight cycles or 16,600 flight hours, to 12,200 flight 
cycles or 18,200 flight hours.
     The compliance times for the initial post-repair 
inspection range from 6,500 flight cycles or 13,900 flight hours, to 
10,200 flight cycles or 15,200 flight hours; and the post-repair 
repetitive inspection interval ranges from 4,700 flight cycles or 
10,000 flight hours, to 11,000 flight cycles or 23,300 flight hours.
    For Model A310 series airplanes:
     The compliance times for the initial inspection range from 
before the accumulation of 3,000 total flight cycles or 14,900 total 
flight hours, to 6,400 total flight cycles or 12,800 total flight 
cycles.
     The compliance times for the repetitive inspection 
interval range from 4,600 flight cycles or 23,800 flight hours, to 
6,200 flight cycles or 12,400 flight hours.
     The initial inspection compliance times for post-doubler 
modified airplanes range from 7,500 flight cycles or 37,200 flight 
hours, to 11,000 flight cycles or 22,000 flight hours after the 
modification; the post-doubler repetitive inspection interval ranges 
from 5,900 flight cycles or 29,500 flight hours, to 6,500 flight cycles 
or 13,000 flight hours.
     The compliance times for the initial post-repair 
inspection range from 4,500 flight cycles or 23,700 flight hours, to 
5,400 flight cycles or 10,800 flight hours; and the post-repair 
repetitive inspection interval ranges from 2,500 flight cycles or 
12,200 flight hours, to 2,800 flight cycles or 5,600 flight hours.

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).
     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. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

[[Page 19507]]

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

    Unlike the procedures described in the following service 
information, this proposed AD would not permit further flight if cracks 
are detected in the lower spar of the engine pylons between ribs 6 and 
7. We have determined that, because of the safety implications and 
consequences associated with that cracking, any cracked lower spar of 
the engine pylons between ribs 6 and 7 must be repaired or modified 
before further flight. This difference has been coordinated with the 
EASA.
     Airbus Service Bulletin A300-54-0073, Revision 03, dated 
October 11, 2012 (for Model A300 series airplanes).
     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).
    Where the ``Grace periods'' specified in paragraph 1.E., 
``Compliance,'' of the service information identified previously 
contain ambiguous language, i.e., ``for aircraft that have already 
exceeded or are close to exceed the threshold or scheduled interval,'' 
this proposed AD does not include that language. We have clarified this 
exception to the service information in paragraph (i)(2) of this 
proposed AD.

Costs of Compliance

    We estimate that this proposed 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 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 $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 proposed 
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 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) 
2000-10-18, Amendment 39-11742 (65 FR 34055, May 26, 2000), and adding 
the following new AD:

Airbus: Docket No. FAA-2016-5039; Directorate Identifier 2013-NM-
148-AD.

(a) Comments Due Date

    We must receive comments by May 20, 2016.

(b) Affected ADs

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

(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 and F4-622R 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 a determination that the inspection 
compliance time and repetitive interval 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 prevent 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 paragraphs 
(g)(1), (g)(2), and (g)(3) of this AD: Do an eddy current or liquid 
penetrant inspection for cracking of the

[[Page 19508]]

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 paragraphs (g)(1), (g)(2), and 
(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 paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD until a repair or modification 
specified in the Accomplishment Instructions of the applicable 
Airbus service bulletin identified in paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD is done.

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


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


    Note 3 to paragraph (g) of this AD: An additional source of 
guidance for accomplishing the modification specified in Airbus 
Service Bulletin A310-54-2017, Revision 06, dated October 3, 2012, 
can be found in Airbus Service Bulletin A310-54-2023, Revision 03, 
dated July 9, 2002.

    (1) Airbus Service Bulletin A300-54-0073, Revision 03, dated 
October 11, 2012 (for Model A300 series airplanes).
    (2) Airbus Service Bulletin A300-54-6014, Revision 07, dated 
September 5, 2012 (for Model A300-600 series airplanes).
    (3) Airbus Service Bulletin A310-54-2017, Revision 06, dated 
October 3, 2012 (for Model A310 series airplanes).

(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 paragraphs (g)(1), (g)(2), and (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 paragraphs (g)(1), (g)(2), and (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 paragraphs (g)(1), (g)(2), and (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 paragraphs (g)(1), 
(g)(2), and (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'' specified in paragraph 1.E., 
``Compliance,'' of the service information, except the language 
``for aircraft that have already exceeded or are close to exceed 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 an 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) 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 (j)(1) through (j)(10) of this AD.
    (1) Airbus Service Bulletin A300-54-0073, Revision 1, dated 
March 28, 1994 (for Model A300 series airplanes), which is 
incorporated by reference in AD 96-11-05, Amendment 39-9630 (61 FR 
26091, May 24, 1996).
    (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 is 
incorporated by reference in AD 96-11-05, Amendment 39-9630 (61 FR 
26091, May 24, 1996).
    (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 is 
incorporated by reference in AD 2000-10-18, Amendment 39-11742 (65 
FR 34055, May 26, 2000).
    (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.

(k) 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]. 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.
    (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

[[Page 19509]]

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.

(l) 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 it in Docket No. FAA-2016-5039.
    (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 [email protected]; 
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 March 24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07569 Filed 4-4-16; 8:45 am]
 BILLING CODE 4910-13-P
Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 19505

(3) Be installed so that escaping Directives issued against the changed 30, West Building Ground Floor, Room
oxygen cannot come in contact with and type design, if any, and a plan for W12–140, 1200 New Jersey Avenue SE.,
cause ignition of grease, fluid, or vapor resolving the unsafe conditions for the Washington, DC 20590.
accumulations that are present in FAA type design. • Hand Delivery: U.S. Department of
normal operation or that may result Issued in Kansas City, Missouri, on March Transportation, Docket Operations, M–
from the failure or malfunction of any 28, 2016. 30, West Building Ground Floor, Room
other system. Mel Johnson, W12–140, 1200 New Jersey Avenue SE.,
Protection of Oxygen Equipment From Acting Manager, Small Airplane Directorate
Washington, DC, between 9 a.m. and 5
Rupture Aircraft Certification Service. p.m., Monday through Friday, except
[FR Doc. 2016–07786 Filed 4–4–16; 8:45 am]
Federal holidays.
(1) Each element of the oxygen system For service information identified in
must have sufficient strength to BILLING CODE 4910–13–P
this NPRM, contact Airbus SAS,
withstand the maximum pressure and Airworthiness Office—EAW, 1 Rond
temperature, in combination with any Point Maurice Bellonte, 31707 Blagnac
externally applied loads arising from DEPARTMENT OF TRANSPORTATION
Cedex, France; telephone +33 5 61 93 36
consideration of limit structural loads 96; fax +33 5 61 93 44 51; email
Federal Aviation Administration
that may be acting on that part of the account.airworth-eas@airbus.com;
system. Internet http://www.airbus.com. You
(2) Oxygen pressure sources and the 14 CFR Part 39
may view this referenced service
lines between the source and the shutoff [Docket No. FAA–2016–5039; Directorate
information at the FAA, Transport
means must be: Identifier 2013–NM–148–AD]
Airplane Directorate, 1601 Lind Avenue
(i) Protected from unsafe RIN 2120–AA64 SW., Renton, WA. For information on
temperatures; and
(ii) Located where the probability and the availability of this material at the
Airworthiness Directives; Airbus FAA, call 425–227–1221.
hazard of rupture in a crash landing are Airplanes
minimized. Examining the AD Docket
AGENCY: Federal Aviation
Hydraulic Systems Administration (FAA), DOT. You may examine the AD docket on
(1) Design. Each hydraulic system the Internet at http://
ACTION: Notice of proposed rulemaking
must be designed as follows: www.regulations.gov by searching for
(NPRM).
(i) Each hydraulic system and its and locating Docket No. FAA–2016–
elements must withstand, without SUMMARY: We propose to supersede 5039; or in person at the Docket
yielding, the structural loads expected airworthiness directive (AD) 2000–10– Management Facility between 9 a.m.
in addition to hydraulic loads. 18, that applies to certain Airbus Model and 5 p.m., Monday through Friday,
(ii) A means to indicate the pressure A300 series airplanes; Model A300 B4– except Federal holidays. The AD docket
in each hydraulic system which 600, B4–600R, F4–600R series airplanes, contains this proposed AD, the
supplies two or more primary functions and Model A300 C4–605R Variant F regulatory evaluation, any comments
must be provided to the flight crew. airplanes (collectively called Model received, and other information. The
(iii) There must be means to ensure A300–600 series airplanes); and Model street address for the Docket Operations
that the pressure, including transient A310 series airplanes. AD 2000–10–18 office (telephone 800–647–5527) is in
(surge) pressure, in any part of the requires repetitive inspections to detect the ADDRESSES section. Comments will
system will not exceed the safe limit cracks in the lower spar of the engine be available in the AD docket shortly
above design operating pressure and to pylons between ribs 6 and 7, and repair after receipt.
prevent excessive pressure resulting if necessary. Since we issued AD 2000– FOR FURTHER INFORMATION CONTACT: Dan
from fluid volumetric changes in all 10–18, we have determined that the Rodina, Aerospace Engineer,
lines which are likely to remain closed compliance times for the initial International Branch, ANM–116,
long enough for such changes to occur. inspection and the repetitive intervals Transport Airplane Directorate, FAA,
(iv) The minimum design burst must be reduced to allow timely 1601 Lind Avenue SW., Renton, WA
pressure must be 2.5 times the operating detection of cracks in the engine pylon’s 98057–3356; telephone (425) 227–2125;
pressure. lower spar between ribs 6 and 7. This fax (425) 227–1149.
(2) Tests. Each system must be proposed AD would reduce the
substantiated by proof pressure tests. SUPPLEMENTARY INFORMATION:
compliance times for the initial
When proof tested, no part of any inspection and the repetitive intervals. Comments Invited
system may fail, malfunction, or We are proposing this AD to prevent
experience a permanent set. The proof We invite you to send any written
fatigue cracking, which could result in relevant data, views, or arguments about
load of each system must be at least 1.5 reduced structural integrity of the
times the maximum operating pressure this proposed AD. Send your comments
engine pylon’s lower spar, and possible to an address listed under the
of that system.
separation of the engine from the ADDRESSES section. Include ‘‘Docket No.
(3) Accumulators. A hydraulic
accumulator or reservoir may be airplane. FAA–2016–5039; Directorate Identifier
installed on the engine side of any DATES: We must receive comments on 2013–NM–148–AD’’ at the beginning of
firewall, if— this proposed AD by May 20, 2016. your comments. We specifically invite
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(i) It is an integral part of an engine ADDRESSES: You may send comments by comments on the overall regulatory,
or propeller system; or any of the following methods: economic, environmental, and energy
(ii) The reservoir is nonpressurized • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
and the total capacity of all such http://www.regulations.gov. Follow the consider all comments received by the
nonpressurized reservoirs is one quart instructions for submitting comments. closing date and may amend this
or less. • Fax: (202) 493–2251. proposed AD based on those comments.
(b) Ultramagic, through EASA, will • Mail: U.S. Department of We will post all comments we
provide the FAA with all Airworthiness Transportation, Docket Operations, M– receive, without change, to http://

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19506 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules

www.regulations.gov, including any in the engine pylon lower spar between ribs flight cycles or 16,600 flight hours, to
personal information you provide. We 6 and 7. 12,200 flight cycles or 18,200 flight
will also post a report summarizing each For the reasons described above, this new hours.
[EASA] AD retains the requirements of DGAC
substantive verbal contact we receive
France AD 1993–228–154(B)R3 and EASA • The compliance times for the initial
about this proposed AD. AD 2008–0001, which are superseded, and post-repair inspection range from 6,500
Discussion requires accomplishment of the [eddy current flight cycles or 13,900 flight hours, to
or liquid penetrant] inspections [for cracking] 10,200 flight cycles or 15,200 flight
On May 16, 2000, we issued AD and, depending on findings, [related hours; and the post-repair repetitive
2000–10–18, Amendment 39–11742 (65 investigative and] corrective actions [repairs], inspection interval ranges from 4,700
FR 34055, May 26, 2000). AD 2000–10– within the new thresholds and intervals flight cycles or 10,000 flight hours, to
18 requires actions intended to address specified in Airbus Service Bulletin (SB) 11,000 flight cycles or 23,300 flight
an unsafe condition on certain Airbus A300–54–0073 Revision 03 [dated October
hours.
Model A300 series airplanes; Model 11, 2012] or SB A310–54–2017 Revision 06
[dated October 3, 2012] or SB A300–54–6014 For Model A310 series airplanes:
A300 B4–600, B4–600R, F4–600R series
Revision 07 [dated September 5, 2012]. • The compliance times for the initial
airplanes, and Model A300 C4–605R
Related investigative actions include inspection range from before the
Variant F airplanes (collectively called
eddy current or liquid penetrant accumulation of 3,000 total flight cycles
Model A300–600 series airplanes); and
inspections for cracking of areas with or 14,900 total flight hours, to 6,400
Model A310 series airplanes.
Since we issued AD 2000–10–18, removed protection. The unsafe total flight cycles or 12,800 total flight
Amendment 39–11742 (65 FR 34055, condition is cracking in the lower spar cycles.
May 26, 2000), we have determined that of the engine pylons between ribs 6 and • The compliance times for the
the compliance times for the initial 7, which could result in reduced repetitive inspection interval range from
inspection and the repetitive intervals structural integrity of the engine pylon’s 4,600 flight cycles or 23,800 flight
must be reduced to allow timely lower spar, and possible separation of hours, to 6,200 flight cycles or 12,400
detection of cracks in the engine pylon’s the engine from the airplane. You may flight hours.
lower spar between ribs 6 and 7. examine the MCAI in the AD docket on • The initial inspection compliance
The European Aviation Safety Agency the Internet at http:// times for post-doubler modified
(EASA), which is the Technical Agent www.regulations.gov by searching for airplanes range from 7,500 flight cycles
for the Member States of the European and locating it in Docket No. FAA– or 37,200 flight hours, to 11,000 flight
Community, has issued EASA 2016–5039. cycles or 22,000 flight hours after the
Airworthiness Directive 2013–0167, The compliance times for the modification; the post-doubler repetitive
dated July 26, 2013 (referred to after this inspections vary, depending on airplane inspection interval ranges from 5,900
as the Mandatory Continuing configuration and utilization as follows. flight cycles or 29,500 flight hours, to
Airworthiness Information, or ‘‘the For Model A300–600 series airplanes: 6,500 flight cycles or 13,000 flight
MCAI’’), to correct an unsafe condition. • The compliance time for the initial hours.
The MCAI states: inspection is before the accumulation of • The compliance times for the initial
Cracks were found between ribs 6 and 7 in 10,900 total flight cycles. post-repair inspection range from 4,500
the lower spar of engine pylons on A310, • The compliance times for the flight cycles or 23,700 flight hours, to
A300 and A300–600 aeroplanes. To prevent repetitive inspection interval are 5,700 5,400 flight cycles or 10,800 flight
crack initiation, a first inspection programme flight cycles for pre-doubler modified hours; and the post-repair repetitive
of this area was rendered mandatory by airplanes; and for post-doubler modified inspection interval ranges from 2,500
DGAC [Direction Générale de l’Aviation airplanes, the compliance times range flight cycles or 12,200 flight hours, to
Civile] France AD 93–228–154 (later revised, from 7,200 flight cycles or 8,200 flight 2,800 flight cycles or 5,600 flight hours.
currently at Revision 3) [http:// hours, to 8,400 flight cycles or 16,000
ad.easa.europa.eu/blob/19932283tb__ Related Service Information Under 1
flight hours.
Superseded.pdf/AD_F-1993-228-154R3_1]
[which corresponds to certain actions in in
• The compliance times for the initial CFR part 51
FAA AD 2000–10–18, Amendment 39–11742 inspection following crack repair range Airbus has issued the following
(65 FR 34055)] for A300 and A300–600 from 5,200 flight cycles or 5,900 flight service bulletins.
aeroplanes. hours, to 6,600 flight cycles or 13,400 • Airbus Service Bulletin A300–54–
At a later date and due to new findings, a flight hours; and the compliance times 0073, Revision 03, dated October 11,
specific inspection programme for A310 for the post-repair repetitive inspection
aeroplanes was rendered mandatory by 2012 (for Model A300 series airplanes).
range from 2,200 flight cycles or 2,500
DGAC France AD 1999–239–287(B) [which • Airbus Service Bulletin A300–54–
flight hours, to 3,400 flight cycles or
corresponds to certain other actions in FAA 6014, Revision 07, dated September 5,
AD 2000–10–18, Amendment 39–11742 (65
6,900 flight hours.
For Model A300 series airplanes: 2012 (for Model A300–600 series
FR 34055, May 26, 2000)]. That [French] AD airplanes).
was later superseded by EASA AD 2008– • The compliance times for the initial
0001 [http://ad.easa.europa.eu/blob/easa_ inspection range from before the • Airbus Service Bulletin A310–54–
ad_2008_0001_Superseded.pdf/AD_2008- accumulation of 4,400 total flight cycles 2017, Revision 06, dated October 3,
0001_1], which introduced new thresholds to 9,400 total flight cycles. 2012 (for Model A310 series airplanes).
and intervals in the frame of the A310 • The compliance times for the This service information describes
extended service goal (ESG) exercise. repetitive inspection interval range from procedures for inspecting for cracking of
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Since DGAC France AD 1993–228– 4,400 flight cycles to 6,100 flight cycles. the engine pylon’s lower spar between
154(B)R3 and EASA AD 2008–0001 were • The initial inspection compliance ribs 6 and 7 and related investigative
issued, a fleet survey and updated Fatigue actions. This service information is
times for post-doubler modified
and Damage Tolerance analyses have been
performed in order to substantiate the second airplanes range from 12,700 flight cycles reasonably available because the
ESG for A300–600, called ESG2 exercise. The or 25,700 flight hours, to 20,700 flight interested parties have access to it
results of these analyses have shown that the cycles or 30,900 flight hours after the through their normal course of business
inspection threshold and interval must be modification; the post-doubler repetitive or by the means identified in the
reduced to allow timely detection of cracks inspection interval ranges from 7,800 ADDRESSES section.

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Document Created: 2018-02-07 13:53:55
Document Modified: 2018-02-07 13:53:55
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by May 20, 2016.
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.
FR Citation		81 FR 19505
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 19505 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 65 (April 5, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
