81 FR 65860 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

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

Page Range		65860-65864
FR Document		2016-22460
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 Issue 186 (Monday, September 26, 2016)
[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
65860 Federal Register / Vol. 81, No. 186 / Monday, September 26, 2016 / Rules and Regulations

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD, DEPARTMENT OF TRANSPORTATION searching for and locating Docket No.
apply. FAA–2016–5039.
(i) The steps labeled as RC, including Federal Aviation Administration
substeps under an RC step and any figures Examining the AD Docket
identified in an RC step, must be done to 14 CFR Part 39 You may examine the AD docket on
comply with the AD. An AMOC is required the Internet at http://
for any deviations to RC steps, including [Docket No. FAA–2016–5039; Directorate www.regulations.gov by searching for
substeps and identified figures. Identifier 2013–NM–148–AD; Amendment and locating Docket No. FAA–2016–
(ii) Steps not labeled as RC may be 39–18659; AD 2016–19–10] 5039; or in person at the Docket
deviated from using accepted methods in Management Facility between 9 a.m.
accordance with the operator’s maintenance RIN 2120–AA64
and 5 p.m., Monday through Friday,
or inspection program without obtaining except Federal holidays. The AD docket
approval of an AMOC, provided the RC steps, Airworthiness Directives; Airbus
Airplanes contains this AD, the regulatory
including substeps and identified figures, can evaluation, any comments received, and
still be done as specified, and the airplane AGENCY: Federal Aviation other information. The address for the
can be put back in an airworthy condition. Administration (FAA), Department of Docket Office (telephone 800–647–5527)
(j) Related Information Transportation (DOT). is Docket Management Facility, U.S.
ACTION: Final rule. Department of Transportation, Docket
For more information about this AD,
contact Brandon Lucero, Aerospace Engineer,
Operations, M–30, West Building
SUMMARY: We are superseding Ground Floor, Room W12–140, 1200
Cabin Safety and Environmental Systems
Airworthiness Directive (AD) 2000–10– New Jersey Avenue SE., Washington,
Branch, ANM–150S, FAA, Seattle Aircraft
18 for certain Airbus Model A300 series DC 20590.
Certification Office (ACO), 1601 Lind Avenue
airplanes; Model A300 B4–600, B4– FOR FURTHER INFORMATION CONTACT: Dan
SW., Renton, WA 98057–3356; phone: 425–
917–6572; fax: 425–917–6590; email:
600R, F4–600R series airplanes, and Rodina, Aerospace Engineer,
Brandon.Lucero@faa.gov.
Model A300 C4–605R Variant F International Branch, ANM–116,
airplanes (collectively called Model Transport Airplane Directorate, FAA,
(k) Material Incorporated by Reference A300–600 series airplanes); and Model 1601 Lind Avenue SW., Renton, WA
(1) The Director of the Federal Register A310 series airplanes. AD 2000–10–18 98057–3356; telephone 425–227–2125;
approved the incorporation by reference required repetitive inspections to detect fax 425–227–1149.
(IBR) of the service information listed in this cracks in the lower spar of the engine
SUPPLEMENTARY INFORMATION:
paragraph under 5 U.S.C. 552(a) and 1 CFR pylons between ribs 6 and 7, and repair
part 51. if necessary. This new AD reduces the Discussion
(2) You must use this service information compliance times for the initial We issued a notice of proposed
as applicable to do the actions required by inspection and the repetitive intervals. rulemaking (NPRM) to amend 14 CFR
this AD, unless the AD specifies otherwise. This AD was prompted by the part 39 to supersede AD 2000–10–18,
(i) Boeing Alert Service Bulletin B787– determination that the compliance times Amendment 39–11742 (65 FR 34055,
81205–SB250054–00, Issue 001, dated for the initial inspection and the May 26, 2000) (‘‘AD 2000–10–18’’). AD
December 19, 2014. repetitive intervals must be reduced to 2000–10–18 applied to certain Airbus
(ii) Reserved. allow timely detection of cracks in the Model A300 series airplanes; Model
(3) For The Boeing Company service engine pylon’s lower spar between ribs A300 B4–600, B4–600R, F4–600R series
information identified in this AD, contact 6 and 7. We are issuing this AD to detect airplanes, and Model A300 C4–605R
Boeing Commercial Airplanes, Attention: and correct fatigue cracking, which Variant F airplanes (collectively called
Data & Services Management, P.O. Box 3707, could result in reduced structural Model A300–600 series airplanes); and
MC 2H–65, Seattle, WA 98124–2207; integrity of the engine pylon’s lower
telephone: 206–544–5000, extension 1; fax:
Model A310 series airplanes. The NPRM
spar, and possible separation of the published in the Federal Register on
206–766–5680; Internet: https:// engine from the airplane.
www.myboeingfleet.com.
April 5, 2016 (81 FR 19505) (‘‘the
DATES: This AD is effective October 31, NPRM’’). The NPRM was prompted by
(4) You may view this service information
2016. a determination that the compliance
at the FAA, Transport Airplane Directorate,
The Director of the Federal Register times for the initial inspection and the
1601 Lind Avenue SW., Renton, WA. For
approved the incorporation by reference repetitive intervals must be reduced to
information on the availability of this
of certain publications listed in this AD allow timely detection of cracks in the
material at the FAA, call 425–227–1221.
as of October 31, 2016. engine pylon’s lower spar between ribs
(5) You may view this service information
that is incorporated by reference at the ADDRESSES: For service information 6 and 7. The NPRM proposed to
National Archives and Records identified in this final rule, contact continue to require repetitive
Administration (NARA). For information on Airbus SAS, Airworthiness Office— inspections to detect cracks in the lower
the availability of this material at NARA, call EAW, 1 Rond Point Maurice Bellonte, spar of the engine pylons between ribs
202–741–6030, or go to: http:// 31707 Blagnac Cedex, France; telephone 6 and 7, and repair if necessary. The
www.archives.gov/federal-register/cfr/ibr- +33 5 61 93 36 96; fax +33 5 61 93 44 NPRM also proposed to reduce the
locations.html. 51; email account.airworth-eas@ compliance times for the initial
airbus.com; Internet http:// inspection and the repetitive intervals.
Issued in Renton, Washington, on www.airbus.com. You may view this We are issuing this AD to detect and
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September 6, 2016. referenced service information at the correct fatigue cracking, which could
Michael Kaszycki, FAA, Transport Airplane Directorate, result in reduced structural integrity of
Acting Manager, Transport Airplane 1601 Lind Avenue SW., Renton, WA. the engine pylon’s lower spar, and
Directorate, Aircraft Certification Service. For information on the availability of possible separation of the engine from
[FR Doc. 2016–22187 Filed 9–23–16; 8:45 am] this material at the FAA, call 425–227– the airplane.
1221. It is also available on the Internet The European Aviation Safety Agency
BILLING CODE 4910–13–P
at http://www.regulations.gov by (EASA), which is the Technical Agent

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for the Member States of the European received on the NPRM and the FAA’s compliance, even though the service
Union, has issued EASA Airworthiness response to each comment. information does provide instructions
Directive 2013–0167, dated July 26, for doing certain repairs. Also, UPS
Request To Revise Applicability
2013 (referred to after this as the suggested we add regulatory material in
Mandatory Continuing Airworthiness United Parcel Service (UPS) requested a note, which is not legally enforceable.
Information, or ‘‘the MCAI’’), to correct that we remove Model A300 F4–622R We have not changed this AD in this
an unsafe condition. The MCAI states: airplanes from the proposed regard.
applicability. UPS stated that the NPRM
Cracks were found between ribs 6 and 7 in Request To Define Average Flight Time
would apply to all Model A300
the lower spar of engine pylons on A310, (AFT) Calculations
A300 and A300–600 aeroplanes. To prevent airplanes except those that have Airbus
crack initiation, a first inspection programme Modification 10599 incorporated in UPS requested that we include a
of this area was rendered mandatory by production. UPS explained that Airbus paragraph to define how AFT is
DGAC [Direction Générale de l’Aviation Modification 10559 was embodied on calculated. UPS explained that
Civile] France AD 93–228–154 (later revised, airplane manufacturer serial number paragraph (g) of the proposed AD has
currently at Revision 3) [which corresponds (MSN) 723 and all subsequent airplane repetitive inspection requirements that
to certain actions in FAA AD 2000–10–18] serial numbers; and that the first Model
for A300 and A300–600 aeroplanes.
use an interval defined in the service
A300 F4–622R airplane with this information that is dependent on
At a later date and due to new findings, a modification embodied was MSN 805.
specific inspection programme for A310 airplane AFT methodology, but that the
We infer that UPS made a NPRM does not define parameters for
aeroplanes was rendered mandatory by
DGAC France AD 1999–239–287(B) [which
typographical error in citing the Airbus how and when the AFT is determined.
corresponds to certain other actions in FAA Modification number and intended to UPS submitted proposed language for
AD 2000–10–18]. That [French] AD was later reference Airbus Modification 10149. calculating AFTs.
superseded by EASA AD 2008–0001, which We agree with the commenter’s request
In regards to the AFT definition, we
introduced new thresholds and intervals in to remove Model A300 F4–622R
have determined that, for the reasons
the frame of the A310 extended service goal airplanes from the applicability. Airbus
(ESG) exercise. stated by the commenter, this AD
has verified that all Model A300 F4–
Since DGAC France AD 1993–228– should define AFT calculations. We
622R airplanes are post-Airbus
154(B)R3 and EASA AD 2008–0001 were have added paragraph (j) to this AD
Modification 10149 and that operators
issued, a fleet survey and updated Fatigue do not need to accomplish the accordingly and redesignated
and Damage Tolerance analyses have been
inspections specified in Airbus Service subsequent paragraphs.
performed in order to substantiate the second
ESG for A300–600, called ESG2 exercise. The Bulletin A300–54–6014, Revision 07, Request To Approve Alternative
results of these analyses have shown that the dated September 5, 2012, on those Methods of Compliance (AMOCs)
inspection threshold and interval must be airplanes. As specified in paragraph (c)
UPS requested that we revise
reduced to allow timely detection of cracks of this AD, this AD does not affect
in the engine pylon lower spar between ribs paragraph (k) of the proposed AD to
airplanes on which Airbus Modification
6 and 7. specify that AMOCs approved
10149 has been incorporated in
For the reasons described above, this new previously for AD 2000–10–18 are
production. We have removed Model
[EASA] AD retains the requirements of DGAC approved as AMOCs for the
A300 F4–622R airplanes from paragraph
France AD 1993–228–154(B)R3 and EASA corresponding provisions of this AD.
AD 2008–0001, which are superseded, and
(c)(4) of this AD. This change has been
coordinated with EASA. We agree with the commenter’s
requires accomplishment of the [eddy current request. We have revised paragraph (l)
or liquid penetrant] inspections [for cracking] Requests To Revise Paragraphs (g), (h), of this AD (referred to as paragraph (k)
and, depending on findings, [related and (i) of the Proposed AD
investigative and] corrective actions [repairs],
in the proposed AD) to specify that
within the new thresholds and intervals UPS requested that we revise AMOCs approved previously for AD
specified in Airbus Service Bulletin (SB) paragraphs (g), (h), and (i) of the 2000–10–18 are approved as AMOCs for
A300–54–0073 Revision 03 [dated October proposed AD, which identify the corresponding provisions of this AD.
11, 2012] or SB A310–54–2017 Revision 06 inspections, corrective actions, and
[dated October 3, 2012] or SB A300–54–6014
Conclusion
exceptions for both pre-repair and post-
Revision 07 [dated September 5, 2012]. repair modification configurations. UPS We reviewed the available data,
Related investigative actions include stated that these paragraphs contain including the comments received, and
eddy current or liquid penetrant information in long, complex sentences determined that air safety and the
inspections for cracking of areas with with cross references to other public interest require adopting this AD
removed protection. The unsafe paragraphs in the proposed AD. UPS with the changes described previously
condition is cracking in the lower spar explained that there is potential for and minor editorial changes. We have
of the engine pylons between ribs 6 and confusion of the ruling requirements determined that these changes:
7, which could result in reduced and opportunities for compliance errors. • Are consistent with the intent that
structural integrity of the engine pylon’s UPS provided suggestions for revising was proposed in the NPRM for
lower spar, and possible separation of certain paragraphs of the proposed AD. correcting the unsafe condition; and
the engine from the airplane. You may We do not agree with the commenter’s • Do not add any additional burden
examine the MCAI in the AD docket on request. We recognize that the actions upon the public than was already
the Internet at http:// specified in the service information and proposed in the NPRM.
www.regulations.gov by searching for this AD are complex. However, this AD
Related Service Information Under 1
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and locating it in Docket No. FAA– uses standard terminology that is legally
CFR Part 51
2016–5039. enforceable. UPS’s suggested revisions
included doing all repairs using a Airbus has issued the following
Comments method approved by the FAA, EASA, or service bulletins.
We gave the public the opportunity to Airbus’s EASA Design Organization • Airbus Service Bulletin A300–54–
participate in developing this AD. The Approval. This suggestion would 0073, Revision 03, dated October 11,
following presents the comments require operators to obtain a method of 2012 (for Model A300 series airplanes).

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• Airbus Service Bulletin A300–54– responsibilities among the various (d) Subject
6014, Revision 07, dated September 5, levels of government. Air Transport Association (ATA) of
2012 (for Model A300–600 series For the reasons discussed above, I America Code 54, Nacelles/pylons.
airplanes). certify that this AD: (e) Reason
• Airbus Service Bulletin A310–54– 1. Is not a ‘‘significant regulatory
2017, Revision 06, dated October 3, action’’ under Executive Order 12866; This AD was prompted by the
2. Is not a ‘‘significant rule’’ under the determination that the compliance times for
2012 (for Model A310 series airplanes). the initial inspection and the repetitive
This service information describes DOT Regulatory Policies and Procedures intervals must be reduced to allow timely
procedures for inspecting for cracking of (44 FR 11034, February 26, 1979); detection of cracks in the engine pylon’s
the engine pylon’s lower spar between 3. Will not affect intrastate aviation in lower spar between ribs 6 and 7. We are
ribs 6 and 7, and related investigative Alaska; and issuing this AD to detect and correct fatigue
actions if cracking is found. This service 4. Will not have a significant cracking, which could result in reduced
information is reasonably available economic impact, positive or negative, structural integrity of the engine pylon’s
because the interested parties have on a substantial number of small entities lower spar, and possible separation of the
under the criteria of the Regulatory engine from the airplane.
access to it through their normal course
of business or by the means identified Flexibility Act. (f) Compliance
in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Comply with this AD within the
compliance times specified, unless already
Costs of Compliance Air transportation, Aircraft, Aviation done.
We estimate that this AD affects 156 safety, Incorporation by reference,
Safety. (g) Inspections and Corrective Actions
airplanes of U.S. registry.
We also estimate that it would take Except as provided by paragraphs (i)(1) and
Adoption of the Amendment (i)(2) of this AD, at the applicable time
about 6 work-hours per product to
Accordingly, under the authority specified in paragraph 1.E., ‘‘Compliance,’’ of
comply with the basic requirements of the applicable Airbus service bulletin
this AD. The average labor rate is $85 delegated to me by the Administrator,
specified in paragraph (g)(1), (g)(2), or (g)(3)
per work hour. Based on these figures, the FAA amends 14 CFR part 39 as of this AD: Do an eddy current or liquid
we estimate the cost of this AD on U.S. follows: penetrant inspection for cracking of the
operators to be $79,560, or $510 per engine pylon’s lower spar between ribs 6 and
product. PART 39—AIRWORTHINESS 7; and do all applicable related investigative
We have received no definitive data DIRECTIVES and corrective actions; in accordance with
that would enable us to provide cost the Accomplishment Instructions of the
■ 1. The authority citation for part 39 applicable Airbus service bulletin specified
estimates for the on-condition actions continues to read as follows: in paragraph (g)(1), (g)(2), or (g)(3) of this AD,
specified in this AD. We have no way except as required by paragraph (i)(3) of this
of determining the number of aircraft Authority: 49 U.S.C. 106(g), 40113, 44701.
AD. Do all applicable related investigative
that might need these actions. § 39.13 [Amended] and corrective actions before further flight.
Authority for This Rulemaking Repeat the inspection of the engine pylon’s
■ 2. The FAA amends § 39.13 by lower spar between ribs 6 and 7 thereafter at
Title 49 of the United States Code removing Airworthiness Directive (AD) the applicable time and intervals specified in
specifies the FAA’s authority to issue 2000–10–18, Amendment 39–11742 (65 paragraph 1.E., ‘‘Compliance,’’ of the
rules on aviation safety. Subtitle I, FR 34055, May 26, 2000), and adding applicable Airbus service bulletin specified
section 106, describes the authority of the following new AD: in paragraph (g)(1), (g)(2), or (g)(3) of this AD
the FAA Administrator. ‘‘Subtitle VII: until a repair or modification specified in the
2016–19–10 Airbus: Amendment 39–18659;
Accomplishment Instructions of the
Aviation Programs,’’ describes in more Docket No. FAA–2016–5039; Directorate
applicable Airbus service bulletin identified
detail the scope of the Agency’s Identifier 2013–NM–148–AD.
in paragraph (g)(1), (g)(2), or (g)(3) of this AD
authority. (a) Effective Date is done.
We are issuing this rulemaking under (1) Airbus Service Bulletin A300–54–0073,
This AD is effective October 31, 2016.
the authority described in ‘‘Subtitle VII, Revision 03, dated October 11, 2012 (for
Part A, Subpart III, Section 44701: (b) Affected ADs Model A300 series airplanes).
General requirements.’’ Under that This AD replaces AD 2000–10–18, Note 1 to paragraph (g)(1) of this AD:
section, Congress charges the FAA with Amendment 39–11742 (65 FR 34055, May 26, Airbus Service Bulletin A300–54–0080,
promoting safe flight of civil aircraft in 2000) (‘‘AD 2000–10–18’’). Revision 02, dated July 9, 2002, is an
air commerce by prescribing regulations additional source of guidance for
(c) Applicability accomplishing the modification specified in
for practices, methods, and procedures
This AD applies to the Airbus airplanes Airbus Service Bulletin A300–54–0073,
the Administrator finds necessary for identified in paragraphs (c)(1) through (c)(6) Revision 03, dated October 11, 2012.
safety in air commerce. This regulation of this AD, certificated in any category,
is within the scope of that authority (2) Airbus Service Bulletin A300–54–6014,
except airplanes on which Airbus Revision 07, dated September 5, 2012 (for
because it addresses an unsafe condition Modification 10149 has been incorporated in Model A300–600 series airplanes).
that is likely to exist or develop on production.
Note 2 to paragraph (g)(2) of this AD:
products identified in this rulemaking (1) Airbus Model A300 B2–1A, B2–1C,
Airbus Service Bulletin A300–54–6020,
action. B2K–3C, B2–203, B4–2C, B4–103, and B4–
Revision 02, dated July 9, 2002, is an
203 airplanes.
Regulatory Findings additional source of guidance for
(2) Airbus Model A300 B4–601, B4–603,
accomplishing the modification specified in
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We determined that this AD will not B4–620, and B4–622 airplanes.
Airbus Service Bulletin A300–54–6014,
have federalism implications under (3) Airbus Model A300 B4–605R and B4–
Revision 07, dated September 5, 2012.
622R airplanes.
Executive Order 13132. This AD will (4) Airbus Model A300 F4–605R airplanes. (3) Airbus Service Bulletin A310–54–2017,
not have a substantial direct effect on (5) Airbus Model A300 C4–605R Variant F Revision 06, dated October 3, 2012 (for
the States, on the relationship between airplanes. Model A310 series airplanes).
the national government and the States, (6) Airbus Model A310–203, –204, –221, Note 3 to paragraph (g)(3) of this AD:
or on the distribution of power and –222, –304, –322, –324, and –325 airplanes. Airbus Service Bulletin A310–54–2023,

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(2) You must use this service information revising the airplane flight manual Docket Management Facility, U.S.
as applicable to do the actions required by (AFM) to advise the flight crew of Department of Transportation, Docket
this AD, unless this AD specifies otherwise. certain operating restrictions for Operations, M–30, West Building
(i) Airbus Service Bulletin A300–54–0073, airplanes equipped with an automatic Ground Floor, Room W12–140, 1200
Revision 03, dated October 11, 2012.
(ii) Airbus Service Bulletin A300–54–6014,
shutoff system; and revising the New Jersey Avenue SE., Washington,
Revision 07, dated September 5, 2012. maintenance program by incorporating DC 20590.
(iii) Airbus Service Bulletin A310–54– new airworthiness limitations for fuel FOR FURTHER INFORMATION CONTACT: Serj
2017, Revision 06, dated October 3, 2012. tank systems to satisfy Special Federal Harutunian, Aerospace Engineer,
(3) For service information identified in Aviation Regulation No. 88 Propulsion Branch, ANM–140L, FAA,
this AD, contact Airbus SAS, Airworthiness requirements. We are issuing this AD to Los Angeles Aircraft Certification Office
Office—EAW, 1 Rond Point Maurice prevent operation of the center and (ACO), 3960 Paramount Boulevard,
Bellonte, 31707 Blagnac Cedex, France; auxiliary tank fuel boost pumps with
telephone +33 5 61 93 36 96; fax +33 5 61
Lakewood, CA 90712–4137; phone:
continuous low pressure, which could 562–627–5254; fax: 562–627–5210;
93 44 51; email account.airworth-
eas@airbus.com; Internet http://
lead to friction sparks or overheating in email: Serj.Harutunian@faa.gov.
www.airbus.com. the fuel pump inlet that could create a SUPPLEMENTARY INFORMATION:
(4) You may view this service information potential ignition source inside the
at the FAA, Transport Airplane Directorate, center and auxiliary fuel tanks. These Discussion
1601 Lind Avenue SW., Renton, WA. For conditions, in combination with We issued a supplemental notice of
information on the availability of this flammable fuel vapors, could result in a proposed rulemaking (SNPRM) to
material at the FAA, call 425–227–1221. fuel tank explosion and consequent loss
(5) You may view this service information amend 14 CFR part 39 by adding an AD
of the airplane. that would apply to all The Boeing
that is incorporated by reference at the
National Archives and Records DATES: This AD is effective October 31, Company Model 737–100, –200, –200C,
Administration (NARA). For information on 2016. –300, –400, and –500 series airplanes.
the availability of this material at NARA, call The Director of the Federal Register The SNPRM published in the Federal
202–741–6030, or go to: http:// approved the incorporation by reference Register on March 28, 2016 (81 FR
www.archives.gov/federal-register/cfr/ibr- of certain publications listed in this AD 17098) (‘‘the SNPRM’’). We preceded
locations.html. as of October 31, 2016. the SNPRM with a notice of proposed
Issued in Renton, Washington, on ADDRESSES: For Boeing service rulemaking (NPRM) that published in
September 12, 2016. information identified in this final rule, the Federal Register on October 12,
Michael Kaszycki, contact Boeing Commercial Airplanes, 2011 (76 FR 63229) (‘‘the NPRM’’). The
Acting Manager, Transport Airplane Attention: Data & Services Management, NPRM proposed to require installing an
Directorate, Aircraft Certification Service. P.O. Box 3707, MC 2H–65, Seattle, WA automatic shutoff system for the center
[FR Doc. 2016–22460 Filed 9–23–16; 8:45 am] 98124–2207; telephone: 206–544–5000, and auxiliary tank fuel boost pumps, as
BILLING CODE 4910–13–P extension 1; fax: 206–766–5680; Internet applicable; installing a placard in the
https://www.myboeingfleet.com. For airplane flight deck if necessary;
BAE Systems service information replacing the P5–2 fuel system module
DEPARTMENT OF TRANSPORTATION identified in this final rule, contact BAE assembly; installing the UCO protection
Systems, Attention: Commercial system for the fuel boost pumps;
Federal Aviation Administration Product Support, 600 Main Street, Room revising the airplane flight manual to
S18C, Johnson City, NY 13790–1806; advise the flight crew of certain
14 CFR Part 39 phone: 607–770–3084; fax: 607–770– operating restrictions for airplanes
[Docket No. FAA–2011–1068; Directorate 3015; email: CS-Customer.Service@ equipped with an automatic shutoff
Identifier 2010–NM–189–AD; Amendment baesystems.com; Internet: http:// system; and revising the maintenance
39–18647; AD 2016–18–16] www.baesystems-ps.com/ program by incorporating new
customersupport. You may view this airworthiness limitations for fuel tank
RIN 2120–AA64
referenced service information at the systems to satisfy Special Federal
Airworthiness Directives; The Boeing FAA, Transport Airplane Directorate, Aviation Regulation No. 88
Company Airplanes 1601 Lind Avenue SW., Renton, WA. requirements. The NPRM was prompted
For information on the availability of by fuel system reviews conducted by the
AGENCY: Federal Aviation this material at the FAA, call 425–227– manufacturer. The SNPRM proposed to
Administration (FAA), DOT. 1221. It is also available on the Internet require updated or additional actions for
ACTION: Final rule. at http://www.regulations.gov by certain airplane configurations. We are
searching for and locating Docket No. issuing this AD to prevent operation of
SUMMARY: We are adopting a new FAA–2011–1068. the center and auxiliary tank fuel boost
airworthiness directive (AD) for all The pumps with continuous low pressure,
Boeing Company Model 737–100, –200, Examining the AD Docket
which could lead to friction sparks or
–200C, –300, –400, and –500 series You may examine the AD docket on overheating in the fuel pump inlet that
airplanes. This AD was prompted by the Internet at http:// could create a potential ignition source
fuel system reviews conducted by the www.regulations.gov by searching for inside the center and auxiliary fuel
manufacturer. This AD requires and locating Docket No. FAA–2011– tanks. These conditions, in combination
installing an automatic shutoff system 1068; or in person at the Docket with flammable fuel vapors, could result
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for the center and auxiliary tank fuel Management Facility between 9 a.m. in a fuel tank explosion and consequent
boost pumps, as applicable; installing a and 5 p.m., Monday through Friday, loss of the airplane.
placard in the airplane flight deck if except Federal holidays. The AD docket
necessary; replacing the P5–2 fuel contains this AD, the regulatory Comments
system module assembly; installing the evaluation, any comments received, and We gave the public the opportunity to
‘‘uncommanded ON’’ (UCO) protection other information. The address for the participate in developing this AD. The
system for the fuel boost pumps; Docket Office (phone: 800–647–5527) is following presents the comments

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Document Created: 2018-02-09 13:22:51
Document Modified: 2018-02-09 13:22:51
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		Rules and Regulations
Action		Final rule.
Dates		This AD is effective October 31, 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 65860
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 65860 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

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

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
