[Federal Register Volume 82, Number 153 (Thursday, August 10, 2017)]
[Proposed Rules]
[Pages 37360-37366]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16051]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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  Federal Register / Vol. 82, No. 153 / Thursday, August 10, 2017 / 
Proposed Rules  

[[Page 37360]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0713; Directorate Identifier 2016-NM-199-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-12-
12, for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-
200, and A340-300 series airplanes; and AD 2013-16-26 for all Airbus 
Model A330-200 Freighter, A330-200 and -300, and A340-200 and -300 
series airplanes. AD 2012-12-12 requires repetitive inspections of the 
outer skin rivets of the cargo doors; repair if necessary; and other 
repetitive inspections. AD 2013-16-26 requires repetitive inspections 
of certain cargo doors, and repair if necessary. Since we issued AD 
2012-12-12 and AD 2013-16-26, we have determined that a new inspection 
procedure is necessary to address the unsafe condition. This proposed 
AD would continue to require repetitive inspections and repair if 
necessary. This proposed AD would add a one-time inspection and 
adjustment of certain hook gaps; reinforcement of the door frame 
structure; related investigative and corrective actions if necessary; 
and a modification, which would allow deferring reinforcement of the 
cargo door structure. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by September 25, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above 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--EAL, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
45 80; 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-2017-
0713; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; 
fax: 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0713; 
Directorate Identifier 2016-NM-199-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On June 7, 2012, we issued AD 2012-12-12, Amendment 39-17092 (77 FR 
37797, June 25, 2012) (``AD 2012-12-12''), for all Airbus Model A330-
200 series airplanes, Model A330-200 Freighter series airplanes, Model 
A330-300 series airplanes, Model A340-200 series airplanes, and Model 
A340-300 series airplanes. AD 2012-12-12 was prompted by reports of 
sheared fasteners located on the outside skin of the forward cargo door 
and cracks on the frame fork ends, as well as cracks of the aft cargo 
door frame 64A. AD 2012-12-12 requires a detailed inspection of the 
outer skin rivets at the frame fork ends of the forward and aft cargo 
doors for sheared, loose, and missing rivets; repair of the outer skin 
rivets if necessary; and other repetitive inspections. We issued AD 
2012-12-12 to detect and correct sheared, loose, or missing fasteners 
on the forward and aft cargo door frame, which could result in the loss 
of structural integrity of the forward and aft cargo door.
    On August 9, 2013, we issued AD 2013-16-26, Amendment 39-17564 (78 
FR 53640, August 30, 2013) (``2013-16-26''), for all Airbus Model A330-
200 Freighter series airplanes, Model A330-200 and -300 series 
airplanes, and Model A340-200 and -300 series airplanes. AD 2013-16-26 
was prompted by reports of cracked adjacent frame forks of a forward 
cargo door. AD 2013-16-26 requires repetitive detailed inspections for 
cracks and sheared, loose, or missing rivets of the forward cargo door 
and, for certain airplanes, of the aft cargo door, and repair if 
necessary. We issued AD 2013-16-26 to detect and correct cracked or 
ruptured cargo door frames, which could result in

[[Page 37361]]

reduced structural integrity of the forward or aft cargo door.
    Since we issued AD 2012-12-12 and AD 2013-16-26, we have determined 
that a new inspection procedure is necessary to address the unsafe 
condition. In addition, the manufacturer has released some terminating 
action modifications for the cargo door structure, and provided 
procedures that allow postponing the structural reinforcement 
modification, which terminate the repetitive inspections.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0188, dated September 21, 2016; corrected September 22, 2016 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''); to correct an unsafe condition for 
certain Airbus Model A330-200 and -300 series airplanes; Model A330-200 
Freighter series airplanes; and Model A340-200, -300, -500, and -600 
series airplanes. The MCAI states:

    Several cases of cracked forward (FWD) and aft (AFT) cargo door 
frames, as well as loose, lost, or sheared rivets, have been 
reported by operators. Investigation showed that these findings are 
due to the low margins with respect to fatigue requirements for the 
AFT/FWD cargo door internal structure. Further analysis determined 
that the cargo door hook adjustment is a contributing factor to this 
issue. In case of a cracked or ruptured (FWD or AFT) cargo door 
frame, the loads will be transferred to the remaining structural 
elements. However, the secondary load path is able to sustain those 
loads only for a limited number of flight cycles (FC).
    This condition, if not detected and corrected, could lead to 
rupture of adjacent vertical frames and consequent reduced 
structural integrity of the FWD or AFT cargo door, possibly 
resulting in a cargo door failure, decompression of the aeroplane 
and injury to occupants.
    To initially address this potential unsafe condition, Airbus 
issued Service Bulletin (SB) A330-52-3043 and SB A340-52-4053 and, 
consequently, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France issued AD 2001-124(B) and AD 2001-126(B), requiring a 
special detailed inspection of A330 and A340 AFT cargo doors. Since 
those [DGAC] ADs were issued, prompted by new occurrences, Airbus 
issued Alert Operators Transmission (AOT) A330-52A3085, AOT A340-
52A4092, AOT A330-52A3084, AOT A340-52A4091, AOT A330-A52L003-12, 
AOT 340-A52L004-12, AOT A330-A52L001-12 and AOT A340-A52L002-12, 
providing instructions to inspect the affected areas of both FWD and 
AFT cargo doors.
    Consequently, EASA issued AD 2011-0007 (later revised) [which 
corresponds to FAA AD 2012-12-12], and AD 2012-0274 [which 
corresponds to FAA AD 2013-16-26], to require repetitive detailed 
visual inspections of AFT and FWD cargo doors at specific frames and 
outer skin at all frame fork ends. Since these EASA ADs were issued, 
Airbus published SB A330-52-3087, SB A330-52-3095, SB A340-52-4095, 
SB A340-52-4101, SB A340-52-5020 and SB A340-52-5023, which took 
over the instructions of the above mentioned AOTs, and introduced 
revised thresholds and intervals. In addition, the inspection 
program was expanded to A340-500/-600 aeroplanes. Taking into 
account experience from inspections accomplished in accordance with 
the applicable Airbus SBs at original issue (listed above), Airbus 
issued Revision 01 of these SBs.
    Consequently, EASA issued AD 2015-0192, which superseded EASA AD 
2011-0007R1 and EASA AD 2012-0274, to require for each FWD and AFT 
cargo door, a one-time inspection/adjustment of the hook gaps ``U'' 
and ``V'', repetitive detailed inspections (DET) of all frame fork 
areas, frame head areas and outer skin areas to detect cracks or 
loose/sheared/missing fasteners, and, depending on findings, 
accomplishment of applicable corrective action(s). In addition, EASA 
AD 2015-0192 expanded the Applicability to Airbus A340-500/-600 
aeroplanes.
    Since EASA AD 2015-0192 was issued, Airbus published Revision 02 
of the inspection SBs, introducing high-frequency eddy-current 
inspection method for the frame forks structure. Airbus also 
determined that the interval for these repetitive inspections could 
be increased. In addition, Airbus released some modifications (mod) 
introducing reinforcements to the cargo door structure improving the 
fatigue characteristics. These modifications and associated SBs 
constitute terminating action for the required repetitive 
inspections. Furthermore, Airbus also published other SBs, 
introducing cold working after oversizing of the fastener holes as a 
means for structural reinforcement. Accomplishment of these SBs 
allows postponement of the required Point of Embodiment (Structural 
Modification Point) for the structural reinforcement modification 
SBs which terminate the repetitive inspection requirement.
    For the reasons described above, this [EASA] AD partially 
retains the requirements of EASA AD 2015-0192, which is superseded, 
and requires for each FWD and AFT cargo door initial and repetitive 
special detailed inspections (SDI) of all frame fork areas and 
detailed inspections (DET) of frame head areas and outer skin areas, 
and a one-time inspection/adjustment of the hook gaps ``U'' and 
``V'' and, depending on findings, the accomplishment of applicable 
corrective action(s). Additionally, this [EASA] AD requires 
reinforcement of the cargo door frame structure, while 
accomplishment of a cold working modification allows to defer the 
reinforcement of the cargo door structure.
    It should be noted that additional inspections exist for the 
cargo doors, as specified in Airbus A330 ALS [Airworthiness 
Limitation Section] Part 2 task 523211-02-01 and task 523211-02-02, 
and in Airbus A340 ALS Part 2 Task 523211-02-01.
    This [EASA] AD is re-published to correct typographical errors 
when referencing Airbus SB A340-52-4118.

    Related investigative actions include detailed inspections and high 
frequency non-destructive test inspections. Corrective actions include 
reaming holes, bushing holes, replacing affected parts, and repairing 
cracks. Additional work includes a one-time inspection of the ``U'' and 
``V'' hook gaps, and if necessary, an adjustment of the hook gaps.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0713.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
    The following service information describes procedures for 
inspecting and repairing the frame fork area at beam 4 and frame head 
area at beam 1 from frame 20B to frame 25 of the forward cargo door, 
and adjusting the hook gaps ``U'' and ``V.'' This service information 
is distinct since it applies to different airplane models.
     Service Bulletin A330-52-3087, Revision 02, including 
Appendix 01, dated February 18, 2016.
     Service Bulletin A340-52-4095, Revision 02, including 
Appendix 01, dated November 29, 2015.
     Service Bulletin A340-52-5020, Revision 02, including 
Appendices 01 and 02, dated November 27, 2015.
    The following service information describes procedures for 
modifying the frame fork area at beam 4 and frame head area at beam 1 
from frame 20B to frame 25 of the forward cargo door frame. This 
service information is distinct since it applies to different airplane 
models and configurations.
     Service Bulletin A330-52-3105, dated February 24, 2016.
     Service Bulletin A330-52-3110, dated February 15, 2016.
     Service Bulletin A330-52-3111, dated February 15, 2016.
     Service Bulletin A340-52-4108, dated February 15, 2016.
     Service Bulletin A340-52-4113, dated February 15, 2016.
     Service Bulletin A340-52-4114, dated February 15, 2016.
    The following service information describes procedures for 
modifying the fastener holes in the forward cargo door frame structure 
by cold working and changing the fastener type and size. This service 
information is distinct since it applies to different airplane models 
and configurations.
     Service Bulletin A330-52-3116, dated April 20, 2016.
     Service Bulletin A330-52-3117, dated April 20, 2016.

[[Page 37362]]

     Service Bulletin A330-52-3118, dated April 20, 2016.
     Service Bulletin A340-52-4119, dated April 20, 2016.
     Service Bulletin A340-52-4120, dated April 20, 2016.
     Service Bulletin A340-52-4121, dated April 20, 2016.
    The following service information describes procedures for 
inspecting the frame fork area at beam 4 and frame head area at beam 1 
of the aft cargo door from frame 60 to frame 64A, adjusting the hook 
gaps ``U'' and ``V,'' and doing corrective actions. This service 
information is distinct since it applies to different airplane models 
and configurations.
     Service Bulletin A330-52-3095, Revision 02, including 
Appendices 01 and 02, dated February 19, 2016.
     Service Bulletin A340-52-4101, Revision 02, including 
Appendices 01 and 02, dated November 27, 2015.
     Service Bulletin A340-52-5023, Revision 02, including 
Appendices 01 and 02, dated November 27, 2015.
    The following service information describes procedures for 
modifying the frame fork and head of the aft cargo door frame from 
frame 59A to frame 65. This service information is distinct since it 
applies to different airplane models and configurations.
     Service Bulletin A330-52-3106, dated February 24, 2016.
     Service Bulletin A330-52-3112, dated February 24, 2016.
     Service Bulletin A330-52-3113, dated February 15, 2016.
     Service Bulletin A330-52-3114, dated February 15, 2016.
     Service Bulletin A340-52-4109, dated February 25, 2016.
     Service Bulletin A340-52-4115, dated February 19, 2016.
    The following service information describes procedures for 
modifying the fastener holes in the aft cargo door frame structure by 
cold working and changing the fastener type and size. This service 
information is distinct since it applies to different airplane models.
     Service Bulletin A330-52-3115, dated April 20, 2016.
     Service Bulletin A340-52-4118, dated April 20, 2016.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type designs.

Costs of Compliance

    We estimate that this proposed AD affects 73 airplanes of U.S. 
registry.
    We estimate that it would take up to 888 work-hours per product to 
comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost up to 
$126,420 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be up to $14,738,700, or up to 
$201,900 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national 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:
0
a. Removing Airworthiness Directive (AD) 2012-12-12, Amendment 39-17092 
(77 FR 37797, June 25, 2012); and AD 2013-16-26, Amendment 39-17564 (78 
FR 53640, August 30, 2013); and
0
b. Adding the following new AD:

Airbus: Docket No. FAA-2017-0713; Directorate Identifier 2016-NM-
199-AD.

(a) Comments Due Date

    We must receive comments by September 25, 2017.

(b) Affected ADs

    This AD replaces AD 2012-12-12, Amendment 39-17092 (77 FR 37797, 
June 25, 2012) (``AD 2012-12-12''); and AD 2013-16-26, Amendment 39-
17564 (78 FR 53640, August 30, 2013) (``AD 2013-16-26'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certified in any category, all 
manufacturer serial numbers, except those on which Airbus 
Modification 202702 and Modification 202790 have been embodied in 
production; and the Airbus airplanes identified in paragraphs (c)(3) 
through (c)(5) of this AD, certified in any category, all 
manufacturer serial numbers.
    (1) Model A330-201, -202, -203, -223, -223F, -243, and -243F 
airplanes.
    (2) Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes.
    (3) Model A340-211, -212, and -213 airplanes.
    (4) Model A340-311, -312, and -313 airplanes.

[[Page 37363]]

    (5) Model A340-541 and -642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by reports of cracked forward and aft cargo 
door frames, and loose, missing, or sheared rivets. We are issuing 
this AD to detect and correct cracked or ruptured cargo door frames, 
which could result in reduced structural integrity of the forward or 
aft cargo door.

(f) Compliance

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

(g) Affected Cargo Doors

    For the purpose of this AD, the affected cargo doors are pre-
modification 202702 (forward cargo door) and pre-modification 202790 
(aft cargo door), and are listed by part number (P/N) in the 
applicable service information identified in paragraph (h)(1) of 
this AD. For post-modification doors, which are not affected by this 
AD, the P/Ns are identified as F52370900XXX (forward cargo door) and 
F52372315XXX (aft cargo door), where ``XXX'' can be a combination of 
any three numerical digits.

(h) Forward Cargo Door Repetitive Inspections

    (1) Before exceeding 5,300 total flight cycles since first 
installation of the forward cargo door on an airplane, or within the 
applicable compliance time specified in table 1 to paragraph (h)(1) 
of this AD, whichever occurs later, except as specified in paragraph 
(q) of this AD: Do all applicable detailed and high frequency eddy 
current (HFEC) inspections of all frame fork areas, frame head 
areas, and outer skin areas of each affected forward cargo door, as 
applicable; in accordance with the Accomplishment Instructions of 
the applicable service information specified in paragraph (h)(1)(i), 
(h)(1)(ii), or (h)(1)(iii) of this AD. Do all applicable related 
investigative actions and corrective actions before further flight 
in accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraph (h)(1)(i), (h)(1)(ii), or 
(h)(1)(iii) of this AD, except as required by paragraph (p) of this 
AD. Repeat the applicable inspections of the frame fork areas, frame 
head areas, and outer skin areas of each affected forward cargo door 
thereafter at intervals not to exceed 1,400 flight cycles.

  Table 1 to Paragraph (h)(1) of This AD--Forward Cargo Door Inspection
                             Compliance Time
------------------------------------------------------------------------
  Airplane condition (on the effective
            date of this AD)                     Compliance time
------------------------------------------------------------------------
Inspected only as specified in Airbus    Within 1,100 flight cycles
 Alert Operator Transmission (AOT) A330-  after the last inspection, but
 52A3085 or AOT A340-52A4092, as          without exceeding 10,600
 applicable.                              flight cycles since first
                                          installation of the forward
                                          cargo door on an airplane.
Inspected as specified in Airbus AOT     Within 1,100 flight cycles
 A330-52A3085 and as specified in AOT     after the last inspection as
 A330-A52L003-12, and the last            specified in AOT A330-52A3085.
 inspection was accomplished as
 specified in AOT A330-A52L003-12.
Inspected as specified in Airbus AOT     Within 1,100 flight cycles
 A330-52A3085 and as specified in AOT     after the last inspection as
 A330-A52L003-12, and the last            specified in AOT A330-A52L003-
 inspection was accomplished as           12.
 specified in AOT A330-52A3085.
Inspected as specified in Airbus AOT     Within 1,100 flight cycles
 A340-52A4092 and as specified in AOT     after the last inspection as
 A340-A52L004-12, and the last            specified in AOT A340-52A4092.
 inspection was accomplished as
 specified in AOT A340-A52L004-12.
Inspected as specified in Airbus AOT     Within 1,100 flight cycles
 A340-52A4092 and as specified in AOT     after the last inspection as
 A340-A52L004-12, and the last            specified in AOT A340-A52L004-
 inspection was accomplished as           12.
 specified in AOT A340-52A4092.
Inspected as specified in the original   There is no compliance time for
 issue of Airbus Service Bulletin (SB)    the initial inspection in
 A330-52-3087, or SB A340-52-4095, or     paragraph (h)(1) of this AD
 SB A340-52-5020, as applicable.          for these airplanes, provided
                                          these airplanes comply with
                                          the actions specified
                                          paragraph (r)(1) of this AD.
Inspected as specified in Revision 01    There is no compliance time for
 of Airbus SB A330-52-3087, or SB A340-   the initial inspection in
 52-4095, or SB A340-52-5020, as          paragraph (h)(1) of this AD
 applicable.                              for these airplanes, provided
                                          these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(2) of this AD.
Inspected as specified in Revision 02    Within 1,400 flight cycles
 of Airbus SB A330-52-3087, or SB A340-   after the last inspection, but
 52-4095, or SB A340-52-5020, as          without exceeding 5,300 total
 applicable.                              flight cycles since first
                                          installation of the forward
                                          cargo door on an airplane.
Never inspected........................  Within 1,100 flight cycles
                                          after the effective date of
                                          this AD, but without exceeding
                                          6,400 flight cycles since
                                          first installation of the
                                          forward cargo door on an
                                          airplane.
------------------------------------------------------------------------

    (i) Airbus Service Bulletin A330-52-3087, Revision 02, dated 
February 18, 2016 (``A330-52-3087, R2'').
    (ii) Airbus Service Bulletin A340-52-4095, Revision 02, dated 
November 29, 2015 (``A340-52-4095, R2'').
    (iii) Airbus Service Bulletin A340-52-5020, Revision 02, dated 
November 27, 2015 (``A340-52-5020, R2'').
    (2) Concurrently with the first inspection required by paragraph 
(h)(1) of this AD: Do a one-time detailed inspection of the hook 
gaps ``U'' and ``V'' of each affected forward cargo door for proper 
adjustment, and, depending on findings, adjust the hook(s), in 
accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraph (h)(2)(i), (h)(2)(ii), or 
(h)(2)(iii) of this AD. Do all required hook gap adjustments before 
further flight.
    (i) A330-52-3087, R2.
    (ii) A340-52-4095, R2.
    (iii) A340-52-5020, R2.

(i) Forward Cargo Door Modification

    (1) Except as specified in paragraph (i)(2) of this AD, before 
exceeding 18,500 total flight cycles since first installation of the 
forward cargo door on an airplane, or within 12 months after the 
effective date of this AD, whichever occurs later: Do reinforcement 
modifications on the frame structure of each affected forward cargo 
door, in accordance with the Accomplishment Instructions of the 
applicable service information specified in paragraphs (i)(1)(i) 
through (i)(1)(vi) of this AD, except as required by paragraph (p) 
of this AD.
    (i) Airbus Service Bulletin A330-52-3105, dated February 24, 
2016 (for certain Model A330-202, -223, and -243 airplanes; and 
Model A330-301, -321, -322, -341, and -342 airplanes).
    (ii) Airbus Service Bulletin A330-52-3110, dated February 15, 
2016 (for certain Model A330-202, -203, -223, and -243 airplanes; 
and Model A330-303, -323, and -343 airplanes).
    (iii) Airbus Service Bulletin A330-52-3111, dated February 15, 
2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F 
airplanes; and Model A330-302, -303, -323, -342, and -343 
airplanes).
    (iv) Airbus Service Bulletin A340-52-4108, dated February 15, 
2016 (for certain

[[Page 37364]]

Model A340-211, -212, and -213 airplanes; and Model A340-311, -312, 
and -313 airplanes).
    (v) Airbus Service Bulletin A340-52-4113, dated February 15, 
2016 (for certain Model A340-312 and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4114, dated February 15, 
2016 (for certain Model A340-313 airplanes).
    (2) Accomplishment of the reinforcement modifications required 
by paragraph (i)(1) of this AD may be deferred, provided that, 
before exceeding 18,500 total flight cycles since first installation 
of the forward cargo door on an airplane, or within 12 months after 
the effective date of this AD, whichever occurs later, but not 
earlier than 14,500 total flight cycles for Model A330 airplanes, or 
12,500 total flight cycles for Model A340 airplanes, cold working is 
accomplished on the frame structure of each affected forward cargo 
door, in accordance with the Accomplishment Instructions of the 
applicable service information specified in paragraphs (i)(2)(i) 
through (i)(2)(vi) of this AD, except as required by paragraph (p) 
of this AD. Modification of an airplane by accomplishment of the 
cold working specified in this paragraph does not constitute 
terminating action for the repetitive inspections required by 
paragraph (h)(1) of this AD.
    (i) Airbus Service Bulletin A330-52-3116, dated April 20, 2016 
(for certain Model A330-202, -223, and -243 airplanes; and Model 
A330-301, -321, -322, -341, and -342 airplanes).
    (ii) Airbus Service Bulletin A330-52-3117, dated April 20, 2016 
(for certain Model A330-202, -203, -223, and -243 airplanes; and 
Model A330-303, -323, and -343 airplanes).
    (iii) Airbus Service Bulletin A330-52-3118, dated April 20, 2016 
(for certain Model A330-202, -203, -223, -223F, -243, and -243F 
airplanes; and Model A330-302, -303, -323, -342, and -343 
airplanes).
    (iv) Airbus Service Bulletin A340-52-4119, dated April 20, 2016 
(for certain Model A340-211, -212, and -213 airplanes; and Model 
A340-311, -312, and -313 airplanes).
    (v) Airbus Service Bulletin A340-52-4120, dated April 20, 2016 
(for certain Model A340-312 and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4121, dated April 20, 2016 
(for certain Model A340-313 airplanes).
    (3) Within 18,500 flight cycles after cold working is 
accomplished on the frame structure of each affected forward cargo 
door as specified in paragraph (i)(2) of this AD: Do the 
reinforcement modifications on the frame structure of each affected 
forward cargo door, 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) Forward Cargo Door Terminating Action

    Modification of an airplane by reinforcement of the cargo door 
frame structure required by paragraph (i)(1) or (i)(3) of this AD 
constitutes terminating action for the repetitive inspections 
required by paragraph (h)(1) of this AD for that airplane.

(k) Definitions of Pre-Modified and Post-Modified Airplanes

    (1) For the purpose of this AD, pre-modified Model A330-200 
series airplanes, Model A330-200 Freighter series airplanes, Model 
A330-300 series airplanes, Model A340-200 series airplanes, and 
Model A340-300 series airplanes are defined as those not having 
Airbus Modification 44852, or Modification 44854 applied in 
production, or being in pre-Airbus Service Bulletin A330-52-3044 or 
pre-Airbus Service Bulletin A340-52-4054 configuration, as 
applicable.
    (2) For the purpose of this AD, post-modification Model A330-200 
series airplanes, Model A330-200 Freighter series airplanes, Model 
A330-300 series airplanes, Model A340-200 series airplanes, and 
Model A340-300 series airplanes are defined as those having Airbus 
Modification 44852 or Modification 44854 applied in production, or 
modified in service as specified in Airbus Service Bulletin A330-52-
3044 or Airbus Service Bulletin A340-52-4054, as applicable.

(l) Aft Cargo Door Repetitive Inspections

    (1) Before exceeding 4,000 total flight cycles for pre-modified 
airplanes, or 12,000 total flight cycles for post-modified 
airplanes, since first installation of the aft cargo door on an 
airplane, as applicable, or within the compliance time specified in 
table 2 to paragraph (l)(1) of this AD or table 3 to paragraph 
(l)(1) of this AD, as applicable, whichever occurs later, except as 
specified in paragraph (q) of this AD: Do all applicable inspections 
of all frame fork areas, frame head areas, and outer skin area of 
each affected aft cargo door, in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD. Do all 
applicable related investigative actions and corrective actions 
before further flight in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD, except 
as required by paragraph (p) of this AD. Repeat the applicable 
inspections thereafter at intervals not to exceed 1,400 flight 
cycles.

    Table 2 to Paragraph (l)(1) of This AD--Aft Cargo Door Inspection
               Compliance Times for Pre-Modified Airplanes
------------------------------------------------------------------------
  Airplane condition (on the effective
            date of this AD)                     Compliance time
------------------------------------------------------------------------
Inspected only as specified in Airbus    Within 550 flight cycles after
 AOT A330-52A3084, or AOT A340-52A4091,   the last inspection, but
 as applicable.                           without exceeding 15,800
                                          flight cycles since first
                                          installation of the aft cargo
                                          door on an airplane.
Inspected as specified in Airbus AOT     Within 550 flight cycles after
 A330-52A3084 and as specified in AOT     the last inspection as
 A330-A52L001-12, and the last            specified in AOT A330-52A3084.
 inspection was accomplished as
 specified in AOT A330-A52L001-12.
Inspected as specified in Airbus AOT     Within 550 flight cycles after
 A330-52A3084 and as specified in AOT     the last inspection as
 A330-A52L001-12, and the last            specified in AOT A330-A52L001-
 inspection was accomplished as           12.
 specified in AOT A330-52A3084.
Inspected as specified in Airbus AOT     Within 550 flight cycles after
 A340-52A4091 and as specified in AOT     the last inspection as
 A340-A52L002-12, and the last            specified in AOT A340-52A4091.
 inspection was accomplished as
 specified in AOT A340-A52L002-12.
Inspected as specified in Airbus AOT     Within 550 flight cycles after
 A340-52A4091 and as specified in AOT     the last inspection as
 A340-A52L002-12, and the last            specified in AOT A340-A52L002-
 inspection was accomplished as           12.
 specified in AOT A340-52A4091.
Inspected as specified in the original   There is no compliance time for
 issue of Airbus SB A330-52-3095, or SB   the initial inspection in
 A340-52-4101, as applicable.             paragraph (l)(1) of this AD
                                          for these airplanes, provided
                                          these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(3) of this AD.
Inspected as specified in Revision 01    There is no compliance time for
 of Airbus SB A330-52-3095, or SB A340-   the initial inspection in
 52-4101, as applicable.                  paragraph (l)(1) of this AD
                                          for these airplanes, provided
                                          these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(4) of this AD.
Inspected as specified in Revision 02    Within 1,400 flight cycles
 of Airbus SB A330-52-3095, or SB A340-   after the last inspection as
 52-4101, as applicable.                  specified in Revision 02 of
                                          Airbus SB A330-52-3095, or SB
                                          A340-52-4101, as applicable
                                          but without exceeding 4,000
                                          flight cycles since first
                                          installation of the aft cargo
                                          door on an airplane, as
                                          applicable.

[[Page 37365]]

 
Never inspected........................  Within 550 flight cycles after
                                          the effective date of this AD,
                                          but without exceeding 4,550
                                          flight cycles since first
                                          installation of the aft cargo
                                          door on an airplane.
------------------------------------------------------------------------


    Table 3 to Paragraph (l)(1) of This AD--Aft Cargo Door Inspection
Compliance Times for Post-Modified Airplanes and Model A340-500 and -600
                                Airplanes
------------------------------------------------------------------------
  Airplane condition (on the effective
            date of this AD)                     Compliance time
------------------------------------------------------------------------
Never inspected........................  Within 550 flight cycles after
                                          the effective date of this AD,
                                          but without exceeding 12,550
                                          flight cycles since first
                                          installation of the aft cargo
                                          door on an airplane.
Inspected as specified in the original   There is no compliance time for
 issue of Airbus SB A330-52-3095 or SB    paragraph (l)(1) of this AD
 A340-52-4101, or SB A340-5023, as        for these airplanes, provided
 applicable.                              these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(3) of this AD.
Inspected as specified in Revision 01    There is no compliance time for
 of Airbus SB A330-52-3095, or SB A340-   paragraph (l)(1) of this AD
 52-4101, or SB A340-5023, as             for these airplanes, provided
 applicable.                              these airplanes comply with
                                          the actions specified in
                                          paragraph (r)(4) of this AD.
Inspected as specified in Revision 02    Within 1,400 flight cycles
 of Airbus SB A330-52-3095, or SB A340-   after the last inspection as
 52-4101, or SB A340-5023, as             specified in Revision 02 of
 applicable.                              Airbus SB A330-52-3095, or SB
                                          A340-52-4101, or SB A340-5023,
                                          as applicable, but without
                                          exceeding 12,000 flight cycles
                                          since first installation of
                                          the aft cargo door on an
                                          airplane.
------------------------------------------------------------------------

    (i) Airbus Service Bulletin A330-52-3095, Revision 02, dated 
February 19, 2016 (``A330-52-3095, R2'').
    (ii) Airbus Service Bulletin A340-52-4101, Revision 02, dated 
November 27, 2015 (``A340-52-4101, R2'').
    (iii) Airbus Service Bulletin A340-52-5023, Revision 02, dated 
November 27, 2015 (``A340-52-5023, R2'').
    (2) Concurrently with the first inspection required by paragraph 
(l)(1) of this AD: Do a one-time detailed inspection of the hook 
gaps ``U'' and ``V'' of each affected aft cargo door for proper 
adjustment and, depending on findings, adjust the hook(s) in 
accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraph (l)(2)(i), (l)(2)(ii), or 
(l)(2)(iii) of this AD. Do all required hook gap adjustments before 
further flight.
    (i) A330-52-3095, R2.
    (ii) A340-52-4101, R2.
    (iii) A340-52-5023, R2.

(m) Modification for Pre-Modified Airplanes

    (1) For pre-modified airplanes, except as specified in paragraph 
(m)(2) of this AD: Before exceeding 18,500 total flight cycles since 
first installation of the aft cargo door on an airplane, or within 
12 months after the effective date of this AD, whichever occurs 
later, do reinforcement modifications, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, 
except as required by paragraph (p) of this AD.
    (i) Airbus Service Bulletin A330-52-3106, dated February 24, 
2016 (for certain Model A330-301, -321, -322, -341, and -342 
airplanes).
    (ii) Airbus Service Bulletin A330-52-3112, dated February 24, 
2016 (for certain Model A330-202 and -223 airplanes; and Model A330-
301, -322, -341, and -342 airplanes).
    (iii) Airbus Service Bulletin A330-52-3113, dated February 15, 
2016 (for certain Model A330-223 and -243 airplanes; and Model A330-
322 and -342 airplanes).
    (iv) Airbus Service Bulletin A330-52-3114, dated February 15, 
2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F 
airplanes; and Model A330-302, -303, -323, -342, and -343 
airplanes).
    (v) Airbus Service Bulletin A340-52-4109, dated February 25, 
2016 (for certain Model A340-211, -212, and -213 airplanes; and 
Model A340-311, -312, and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4115, dated February 19, 
2016 (for certain Model A340-212, -213, and -313 airplanes).
    (2) Accomplishment of the reinforcement modifications required 
by paragraph (m)(1) of this AD may be deferred provided that before 
exceeding 18,500 total flight cycles since first installation of the 
aft cargo door on an airplane, or within 12 months after the 
effective date of this AD, whichever occurs later, but not earlier 
than 14,500 total flight cycles, cold working is accomplished on the 
frame structure of each affected aft cargo door, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-52-
3115, dated April 20, 2016; or Airbus Service Bulletin A340-52-4118, 
dated April 20, 2016; as applicable. Modification of an airplane by 
accomplishment of the cold working specified in this paragraph does 
not constitute terminating action for the repetitive inspections 
required by paragraph (l)(1) of this AD.
    (3) For an airplane on which the cold working on the cargo door 
frame structure is accomplished, as specified in paragraph (m)(2) of 
this AD: Within 18,500 flight cycles after the application of cold 
working, do reinforcement modifications, in accordance with the 
Accomplishment Instructions of the service information specified in 
paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, as applicable, 
or using a method approved by the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's 
EASA DOA.

(n) Aft Cargo Door Terminating Action

    Modification of an airplane by reinforcement of the cargo door 
frame structure required by paragraph (m)(1) or (m)(3) of this AD 
constitutes terminating action for the repetitive inspections 
required by paragraph (l)(1) of this AD for that airplane.

(o) Optional Terminating Action Modification for Post-Modified 
Airplanes

    For post-modified airplanes, modification of an airplane by 
reinforcement of the cargo door frame structure, in accordance with 
the Accomplishment Instructions of the applicable service 
information specified in paragraphs (m)(1)(i) through (m)(1)(vi) of 
this AD, or using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA, constitutes terminating action for the repetitive 
inspections required by paragraph (l)(1) of this AD.

(p) Exception to Service Information

    Where the service information specified in paragraphs (h)(1), 
(i)(1), (i)(2), (l)(1), and (m) of this AD specifies to contact 
Airbus for instructions or repair, before further flight, accomplish 
corrective actions in accordance with the procedures specified in 
paragraph (s)(2) of this AD.

[[Page 37366]]

(q) Exception to Initial Inspection Compliance Time

    For the purposes of table 1 to paragraph (h)(1) of this AD, 
table 2 to paragraph (l)(1) of this AD, and table 3 to paragraph 
(l)(1) of this AD: As soon as a cargo door is inspected using any 
applicable service information specified in this AD, the previous 
inspections accomplished in accordance with any alert operator 
transmission can be disregarded for the determination of the 
compliance time for the initial inspection required by this AD.

(r) Credit for Previous Actions

    (1) This paragraph provides credit for the initial inspection 
required by paragraph (h) of this AD, if that inspection was 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-52-3087, dated August 29, 2013; Airbus Service 
Bulletin A340-52-4095, dated August 29, 2013; or Airbus Service 
Bulletin A340-52-5020, dated August 29, 2013; as applicable; 
provided that the actions identified as ``additional work'' in the 
Accomplishment Instructions of Airbus Service Bulletin A330-52-3087, 
Revision 01, dated July 9, 2014; Airbus Service Bulletin A340-52-
4095, Revision 01, dated July 28, 2014; or Airbus Service Bulletin 
A340-52-5020, Revision 01, dated July 9, 2014; as applicable; are 
accomplished within 1,100 flight cycles after that inspection; and 
provided the next inspection of all frame fork areas, frame head 
areas, and outer skin area of each affected forward cargo door is 
accomplished within 1,100 flight cycles after that inspection, in 
accordance with the Accomplishment Instructions of A330-52-3087, R2; 
A330-52-3095, R2; or A340-52-5020, R2, as applicable.
    (2) This paragraph provides credit for the initial inspection 
required by paragraph (h) of this AD, if that inspection was 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-52-3087, Revision 01, dated July 9, 2014; Airbus 
Service Bulletin A340-52-4095, Revision 01, dated July 28, 2014; or 
Airbus Service Bulletin A340-52-5020, Revision 01, dated July 9, 
2014; as applicable; provided that the next inspection of all frame 
fork areas, frame head areas, and outer skin area of each affected 
forward cargo door, is accomplished within 1,100 flight cycles after 
that inspection in accordance with the Accomplishment Instructions 
of A330-52-3087, R2; A330-52-3095, R2; or A340-52-5020, R2, as 
applicable.
    (3) This paragraph provides credit for the initial inspection 
required by paragraph (l) of this AD, if that inspection was 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-52-3095, dated August 29, 2013; Airbus Service 
Bulletin A340-52-4101, dated August 29, 2013; or Airbus Service 
Bulletin A340-52-5023, dated August 29, 2013; provided that the 
actions identified as ``additional work'' in the Accomplishment 
Instructions of Airbus Service Bulletin A330-52-3095, Revision 01, 
dated July 28, 2014; Airbus Service Bulletin A340-52-4101, Revision 
01, dated July 28, 2014; or Airbus Service Bulletin A340-52-5023, 
Revision 01, dated July 28, 2014; as applicable; are accomplished 
within 550 flight cycles after that inspection, and provided the 
next inspection of all frame fork areas, frame head areas, and outer 
skin area of each affected aft cargo door is accomplished within 550 
flight cycles after that inspection in accordance with the 
Accomplishment Instructions of A330-52-3095, R2; A340-52-4101, R2; 
or A340-52-5023, R2, as applicable.
    (4) This paragraph provides credit for the initial inspection 
required by paragraph (l) of this AD, if that inspection was 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-52-3095, Revision 01, dated July 28, 2014; Airbus 
Service Bulletin A340-52-4101, Revision 01, dated July 28, 2014; or 
Airbus Service Bulletin A340-52-5023, Revision 01, dated July 28, 
2014; as applicable; provided that the next inspection of all frame 
fork areas, frame head areas, and outer skin area of each affected 
aft cargo door is accomplished within 550 flight cycles after that 
inspection in accordance with the Accomplishment Instructions of 
A330-52-3095, R2; A340-52-4101, R2; or A340-52-5023, R2, as 
applicable.

(s) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Branch, send it to the 
attention of the person identified in paragraph (t)(2) of this AD. 
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.
    (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.
    (3) Required for Compliance (RC): Except as required by 
paragraph (p) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0188, dated September 21, 2016; corrected 
September 22, 2016, 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-2017-0713.
    (2) For more information about this AD, contact, Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; 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 July 19, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-16051 Filed 8-9-17; 8:45 am]
 BILLING CODE 4910-13-P