81 FR 78899 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 218 (November 10, 2016)

We are superseding Airworthiness Directive (AD) 2010-04-03 for all Airbus Model A310 series airplanes. AD 2010-04-03 required accomplishing repetitive detailed inspections for cracking around the fastener holes in certain wing top skin panels between the front and rear spars on the left- and right-hand sides of the fuselage, and repair if necessary. This new AD continues to require the repetitive detailed inspections, and also requires supplemental repetitive ultrasonic inspections for cracking around the fastener holes in wing top skin panels 1 and 2 at ribs 2 and 3, and repair if necessary. This AD was prompted by development of an ultrasonic inspection program to allow for earlier crack detection and extended repetitive inspection intervals. We are issuing this AD to detect and correct fatigue cracking around the fastener holes, which could result in reduced structural integrity of the airplane.

[Federal Register Volume 81, Number 218 (Thursday, November 10, 2016)]
[Rules and Regulations]
[Pages 78899-78902]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-26810]



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Federal Register / Vol. 81, No. 218 / Thursday, November 10, 2016 / 
Rules and Regulations

[[Page 78899]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3985; Directorate Identifier 2014-NM-182-AD; 
Amendment 39-18708; AD 2016-23-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2010-04-03 for 
all Airbus Model A310 series airplanes. AD 2010-04-03 required 
accomplishing repetitive detailed inspections for cracking around the 
fastener holes in certain wing top skin panels between the front and 
rear spars on the left- and right-hand sides of the fuselage, and 
repair if necessary. This new AD continues to require the repetitive 
detailed inspections, and also requires supplemental repetitive 
ultrasonic inspections for cracking around the fastener holes in wing 
top skin panels 1 and 2 at ribs 2 and 3, and repair if necessary. This 
AD was prompted by development of an ultrasonic inspection program to 
allow for earlier crack detection and extended repetitive inspection 
intervals. We are issuing this AD to detect and correct fatigue 
cracking around the fastener holes, which could result in reduced 
structural integrity of the airplane.

DATES: This AD is effective December 15, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 15, 
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-2015-
3985.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3985; 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 supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2010-04-03, Amendment 39-16196 (75 
FR 6852, February 12, 2010) (``AD 2010-04-03''). AD 2010-04-03 applied 
to all Airbus Model A310 series airplanes. The SNPRM published in the 
Federal Register on July 11, 2016 (81 FR 44812) (``the SNPRM''). We 
preceded the SNPRM with a notice of proposed rulemaking (NPRM) that 
published in the Federal Register on October 13, 2015 (80 FR 61327) 
(``the NPRM''). The NPRM was prompted by development of an ultrasonic 
inspection program to allow for earlier crack detection and extended 
repetitive inspection intervals. The NPRM proposed to retain the 
requirements of AD 2010-04-03, and proposed to require supplemental 
repetitive ultrasonic inspections for cracking around the fastener 
holes in wing top skin panels 1 and 2 at rib 2, and repair if 
necessary. The SNPRM proposed to expand the inspection area to include 
rib 3 due to widespread fatigue damage. We are issuing this AD to 
detect and correct fatigue cracking around the fastener holes, which 
could result in reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0005, dated January 7, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A310 
series airplanes. The MCAI states:

    Following scheduled maintenance, cracks were found around the 
wing top skin panels fastener holes at Rib 2, between Stringer (STG) 
2 and STG14.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane. The General Visual Inspection 
required by the existing applicable Airworthiness Limitation Items 
(ALI) tasks may not be adequate to detect these cracks.
    To address this issue, Airbus developed an inspection programme 
based on repetitive detailed inspections (DET) to ensure that any 
visible cracks in the wing top skin panels 1 and 2 along Rib 2 are 
detected in time and repaired appropriately. EASA issued AD 2008-
0211 to require implementation of this inspection programme.
    After that [EASA] AD was issued, Airbus improved the inspection 
programme with an ultrasonic inspection to allow earlier crack 
detection, to subsequently reduce the scope of potential repair 
action, and to extend the intervals of the repetitive inspections.
    Consequently, EASA issued AD 2014-0200 (later revised), 
superseding [EASA] AD 2008-0211, retaining its requirements, and to 
require supplementary repetitive ultrasonic inspections [for 
cracking] of the wing top skin panel 1 and 2 between STG2 and STG10 
at Rib 2 [and repair if needed].
    Since EASA AD 2014-0020R1 was issued, a widespread fatigue 
damage analysis concluded that the inspection programme has to be 
extended to include the wing top skin panels at Rib 3 attachments. 
For the reasons described above, this [EASA] AD

[[Page 78900]]

retains the requirements of EASA AD 2014-0200R1, which is 
superseded, and extends the inspection area to include Rib 3.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3985.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM or on the determination 
of the cost to the public.

Clarification of Requirements

    We have clarified the terminating action sentence in paragraph (k) 
of this AD by adding a reference to paragraph (g) of this AD.
    We have clarified the average flight time in paragraph (l)(3) of 
this AD for subsequent inspections after the second inspection 
interval.

Conclusion

    We reviewed the relevant data 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 
minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR part 51

    Airbus has issued Service Bulletin A310-57-2096, Revision 03, dated 
June 30, 2015. This service information describes procedures for 
detailed and ultrasonic inspections for cracking around the fastener 
holes of wing top skin panels 1 and 2, at ribs 2 and 3, on the left- 
and right-hand sides of the fuselage. 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 28 airplanes of U.S. registry.
    We also estimate that it takes about 8 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 $19,040, or $680 per product.
    We estimate that it takes about 15 work-hours per product to do any 
necessary on-condition actions that are required based on the results 
of the inspections. Required parts will cost about $10,000 per product. 
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) 
2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010), and 
adding the following new AD:

2016-23-01 Airbus: Amendment 39-18708; Docket No. FAA-2015-3985; 
Directorate Identifier 2014-NM-182-AD.

(a) Effective Date

    This AD is effective December 15, 2016.

(b) Affected ADs

    This AD replaces AD 2010-04-03, Amendment 39-16196 (75 FR 6852, 
February 12, 2010) (``AD 2010-04-03'').

(c) Applicability

    This AD applies to all Airbus Model A310-203, -204, -221, -222, 
-304, -322, -324, and -325 airplanes, certificated in any category, 
all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by the development of an ultrasonic 
inspection program to allow for earlier crack detection and extended 
repetitive inspection intervals. We are issuing this AD to detect 
and correct fatigue cracking around the fastener holes in certain 
wing top skin panels between the front and rear spars on the left- 
and right-hand sides of the fuselage, which could result in reduced 
structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Except as required by paragraph (i) of this AD: Within the 
initial compliance time and thereafter at the repetitive intervals 
specified in paragraphs (h)(1) through (h)(3) of this AD, as 
applicable, accomplish the actions specified in paragraphs (g)(1) 
and (g)(2) of this AD concurrently and in sequence, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A310-57-2096, Revision 03, dated June 30, 2015, except as provided 
by paragraph (j) of this AD.
    (1) Accomplish a detailed inspection for cracking around the 
fastener holes in the wing top skin panels 1 and 2, along ribs 2 and 
3, between the front and rear spars on the left- and right-hand 
sides of the fuselage.
    (2) Accomplish an ultrasonic inspection for cracking around the 
fastener holes in the wing top skin panels 1 and 2, along ribs 2 and 
3, between stringer (STG) 2 and STG10

[[Page 78901]]

on the left- and right-hand sides of the fuselage.

(h) Compliance Times for Airplanes Not Previously Inspected

    (1) For Model A310-203, -204, -221, and -222 airplanes: Do the 
actions required by paragraphs (g)(1) and (g)(2) of this AD at the 
later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii) 
of this AD. Repeat the inspections specified in paragraphs (g)(1) 
and (g)(2) of this AD thereafter at intervals not to exceed 2,000 
flight cycles or 4,100 flight hours, whichever occurs first.
    (i) Prior to the accumulation of 18,700 flight cycles or 37,400 
flight hours since first flight of the airplane, whichever occurs 
first.
    (ii) Within 30 days after the effective date of this AD.
    (2) For Model A310-304, -322, -324, and -325 airplanes having an 
average flight time (AFT) of less than 4 hours: Do the actions 
required by paragraphs (g)(1) and (g)(2) of this AD at the later of 
the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this 
AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) 
of this AD thereafter at intervals not to exceed 2,000 flight cycles 
or 5,600 flight hours, whichever occurs first.
    (i) Prior to the accumulation of 17,300 flight cycles or 48,400 
flight hours since first flight of the airplane, whichever occurs 
first.
    (ii) Within 30 days after the effective date of this AD.
    (3) For Model A310-304, -322, -324, and -325 airplanes having an 
AFT of equal to or more than 4 hours: Do the actions required by 
paragraphs (g)(1) and (g)(2) of this AD at the later of the times 
specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. Repeat 
the inspections specified in paragraphs (g)(1) and (g)(2) of this AD 
thereafter at intervals not to exceed 1,500 flight cycles or 7,500 
flight hours, whichever occurs first.
    (i) Prior to the accumulation of 12,800 flight cycles or 64,300 
flight hours since first flight of the airplane, whichever occurs 
first.
    (ii) Within 30 days after the effective date of this AD.

(i) Compliance Times for Airplanes Previously Inspected

    For airplanes previously inspected before the effective date of 
this AD using Airbus Service Bulletin A310-57-2096, dated May 6, 
2008; Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010; or Airbus Service Bulletin A310-57-2096, Revision 
02, dated March 5, 2014: At the applicable compliance times 
specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, 
accomplish the actions specified in paragraphs (g)(1) and (g)(2) 
concurrently and in sequence, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A310-57-2096, Revision 03, 
dated June 30, 2015. Repeat the inspections specified in paragraphs 
(g)(1) and (g)(2) of this AD thereafter at the repetitive intervals 
specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as 
applicable.
    (1) For Model A310-203, -204, -221, and -222 airplanes: Do the 
actions required by paragraphs (g)(1) and (g)(2) of this AD within 
3,500 flight hours or 1,700 flight cycles, whichever occurs first 
since the most recent inspection.
    (2) For Model A310-304, -322, -324, and -325 airplanes having an 
AFT of less than 4 hours: Do the actions required by paragraphs 
(g)(1) and (g)(2) of this AD within 4,600 flight hours or 1,600 
flight cycles, whichever occurs first since the most recent 
inspection.
    (3) For Model A310-304, -322, -324, and -325 airplanes having an 
AFT of equal to or more than 4 hours: Do the actions required by 
paragraphs (g)(1) and (g)(2) of this AD within 6,100 flight hours or 
1,200 flight cycles, whichever occurs first since the most recent 
inspection.

(j) Compliance Times if No Ultrasonic Equipment is Available

    If no ultrasonic equipment is available for the initial or 
second inspection required by paragraph (g) or (h) of this AD, 
accomplish the detailed inspection specified in paragraph (g)(1) of 
this AD within the applicable compliance times specified in 
paragraphs (j)(1) and (j)(2) of this AD. After accomplishing the 
detailed inspection, do the inspections specified in paragraphs 
(g)(1) and (g)(2) of this AD at the applicable compliance times 
specified by paragraphs (i)(1), (i)(2), and (i)(3) of this AD. 
Subsequently, repeat the inspections specified in paragraphs (g)(1) 
and (g)(2) of this AD thereafter at the applicable repetitive 
intervals specified in paragraphs (h)(1), (h)(2), and (h)(3) of this 
AD.
    (1) For airplanes not previously inspected before the effective 
date of this AD using the service information identified in 
paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do the 
actions required by paragraph (g)(1) of this AD within the initial 
compliance time specified by paragraphs (h)(1), (h)(2), and (h)(3) 
of this AD, as applicable.
    (2) For airplanes previously inspected before the effective date 
of this AD using the service information identified in paragraph 
(j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do the actions 
required by paragraph (g)(1) of this AD within the applicable 
compliance times specified in paragraphs (i)(1), (i)(2), and (i)(3) 
of this AD.
    (i) Airbus Service Bulletin A310-57-2096, dated May 6, 2008.
    (ii) Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010.
    (iii) Airbus Service Bulletin A310-57-2096, Revision 02, dated 
March 5, 2014.

(k) Repair of Cracking

    If any cracking is found during any inspection required by 
paragraph (g), (h), (i), or (j) of this AD, before further flight, 
repair the cracking 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). Accomplishing the repair 
specified in this paragraph terminates the repetitive inspections 
required by paragraph (g), (h), (i), or (j) of this AD, as 
applicable, for the repaired area only.

(l) Definition of Average Flight Time (AFT)

    For the purposes of this AD, the AFT should be established as 
specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD for 
the determination of the compliance times.
    (1) The inspection threshold is defined as the total flight 
hours accumulated (counted from take-off to touch-down), divided by 
the total number of flight cycles accumulated at the effective date 
of this AD.
    (2) The initial inspection interval is defined as the total 
flight hours accumulated divided by the total number of flight 
cycles accumulated at the time of the initial inspection threshold.
    (3) The second inspection interval is defined as the total 
flight hours accumulated divided by the total number of flight 
cycles accumulated between the initial and second inspection 
threshold. For all inspection intervals onwards, the average flight 
time is the flight hours divided by the flight cycles accumulated 
between the last two inspections.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g)(1) of this AD, if those actions were performed before 
the effective date of this AD using the applicable service 
information identified in paragraph (m)(1), (m)(2), or (m)(3) of 
this AD.
    (1) Airbus Service Bulletin A310-57-2096, dated May 6, 2008, 
which was incorporated by reference in AD 2010-04-03.
    (2) Airbus Service Bulletin A310-57-2096, Revision 01, dated 
August 5, 2010, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A310-57-2096, Revision 02, dated 
March 5, 2014, which is not incorporated by reference in this AD.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by 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.

[[Page 78902]]

    (3) Required for Compliance (RC): Except as required by 
paragraph (k) 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0005, dated January 7, 
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-2015-3985.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(4) and (p)(5) of this AD.

(p) 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.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
December 15, 2016.
    (i) Airbus Service Bulletin A310-57-2096, Revision 03, dated 
June 30, 2015.
    (ii) Reserved.
    (4) 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.
    (5) 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.
    (6) 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 October 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-26810 Filed 11-9-16; 8:45 am]
 BILLING CODE 4910-13-P