
[Federal Register Volume 82, Number 37 (Monday, February 27, 2017)]
[Rules and Regulations]
[Pages 11791-11795]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03267]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6896; Directorate Identifier 2016-NM-016-AD; 
Amendment 39-18805; AD 2017-04-10]
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 adopting a new airworthiness directive (AD) for all 
Airbus Model A318-111, and -112 airplanes; Model A319-111, -112, -113, 
-114, and -115 airplanes; Model A320-211, -212 and -214 airplanes; and 
Model A321-111, -112, -211, -212, and -213 airplanes. This AD was 
prompted by a report of a production quality deficiency on the inner 
retainer installed on link assemblies of the aft engine mount, which 
could result in failure of the retainer. This AD requires an inspection 
for, and replacement of, all non-conforming aft engine mount retainers. 
We are issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective April 3, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 3, 
2017.

ADDRESSES: For Airbus service information identified in this final 
rule, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; 
Internet: http://www.airbus.com.
    For Goodrich service information identified in this final rule, 
contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula 
Vista, CA 91910-2098; telephone: 619-691-2719; email: 
jan.lewis@goodrich.com; Internet: http://www.goodrich.com/TechPubs.
    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-
6896.

[[Page 11792]]

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-
6896; 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 street 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; 
fax: 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A318-111, 
and -112 airplanes, Model A319-111, -112, -113, -114, and -115 
airplanes, Model A320-211, -212 and -214 airplanes, and Model A321-111, 
-112, -211, -212, and -213 airplanes. The NPRM published in the Federal 
Register on May 31, 2016 (81 FR 34287) (``the NPRM''). The NPRM was 
prompted by a report of a production quality deficiency on the inner 
retainer installed on link assemblies of the aft engine mount, which 
could result in failure of the retainer. The NPRM proposed to require 
an inspection for, and replacement of, all non-conforming aft engine 
mount retainers. We are issuing this AD to detect and correct non-
conforming retainers of the aft engine mount. This condition could 
result in the loss of the locking feature of the nuts of the inner and 
outer pins; loss of the pins will result in the aft mount engine link 
no longer being secured to the aft engine mount, possibly resulting in 
damage to 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 2016-0010R1, dated February 16, 2016 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318-111, and -112 airplanes; Model A319-111, -112, -113, -114, and -
115 airplanes; Model A320-211, -212, and -214 airplanes; and Model 
A321-111, -112, -211, -212, and -213 airplanes. The MCAI states:

    During in-service inspections, several aft engine mount inner 
retainers, fitted on aeroplanes equipped with CFM56-5A/5B engines, 
have been found broken. The results of the initial investigations 
highlighted that two different types of surface finish had been 
applied (respectively bright and dull material finishes), and that 
dull finish affects the strength of the retainer with regard to 
fatigue properties of the part. The pins which attach the engine 
link to the aft mount are secured by two nuts, which do not have a 
self-locking feature; this function is provided by the retainer 
brackets. In case of failure of the retainer bracket, the locking 
feature of the nuts of the inner and outer pins is lost; as a 
result, these nuts could subsequently become loose.
    In case of full loss of the nuts, there is the potential to also 
lose the pins, in which case the aft mount link will no longer be 
secured to the aft engine mount. The same locking feature is used 
for the three link assemblies of the aft mount.
    This condition, if not detected and corrected, could lead to in-
flight loss of an aft mount link, possibly resulting in damage to 
the aeroplane and/or injury to persons on the ground.
    To address this potential unsafe condition, EASA issued AD 2013-
0050 [which corresponds to FAA AD 2014-14-06, Amendment 39-17901 (79 
FR 42655, July 23, 2014)] to require a detailed inspection (DET) of 
the aft engine mount inner retainers and the replacement of all 
retainers with dull finish with retainers having a bright finish. 
Since that [EASA] AD was issued, inspection results showed that the 
main cause of crack initiation remains the vibration dynamic effect 
that affects both retainers, either with ``dull'' or ``bright'' 
surface finishes. The non-conforming ``dull'' surface's pitting is 
an aggravating factor. Consequently, EASA issued AD 2015-0021 [which 
corresponds to FAA NPRM Docket No. FAA-2015-3632; Directorate 
Identifier 2015-NM-023-AD (80 FR 55798, September 7, 2015)], 
retaining the requirements of EASA AD 2013-0050, which was 
superseded, and requiring repetitive DET of all aft engine mount 
inner retainers and, depending on findings, their replacement.
    Since that [EASA] AD was issued, a production quality deficiency 
was identified by Airbus and UTAS (formerly Goodrich Aerostructures, 
the engine mount retainer manufacturer) on the delivery of the inner 
retainer, Part Number (P/N) 238-0252-505, installed in the three 
Link assemblies of the engine mount fitted on CFM56-5A/5B engines. 
Airbus issued AOT A71N011-15 and SB A320-71-1070 providing a list of 
affected parts and applicable corrective actions.
    Consequently, EASA issued AD 2016-0010, retaining the 
requirements of EASA AD 2015-0021, which was superseded, and in 
addition requiring the identification and replacement of all non-
conforming aft engine mount inner retainers.
    Since that [EASA] AD was issued, AOT A71N011-15 was revised, 
removing errors and reducing the list of affected parts.
    For the reason described above, this [EASA] AD is revised, 
adding reference to the revised AOT, and removing [EASA] AD 
appendixes, which content is included in the referenced Airbus 
documentation.
    This [EASA] AD is still considered to be an interim action, 
pending development and availability of a final solution.

    This AD requires an inspection for, and replacement of, all non-
conforming aft engine mount retainers. 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-2016-6896.

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 Remove Part Identification Requirement

    Delta Airlines (DAL) requested that we remove the requirement to do 
an inspection to determine the part number of each engine mount inner 
retainer specified in paragraph (g) of the proposed AD. DAL stated that 
Airbus Service Bulletin A320-71-1070, dated November 23, 2015, does not 
specify identifying the part number. DAL stated that identifying the 
part number has no value in determining the affected population of non-
conforming retainers. DAL also requested that we revise the records 
review language in paragraph (g) of the proposed AD to reference the 
criteria in paragraphs (g)(1), and (g)(2), and (g)(3) of the proposed 
AD instead of referring to the part number.
    We do not agree with DAL's request to remove the inspection 
required by paragraph (g) of this AD. However, we do agree that the 
inspection language should be clarified. Paragraph (g) of this AD, 
which corresponds with the MCAI, requires doing actions in accordance 
with Airbus Service Bulletin A320-71-1070, dated November 23, 2015, 
which specifies to determine if there is a non-compliant engine mount 
inner retainer. We have revised paragraph (g) of this AD accordingly.

Request To Clarify Engine Mount Retainer

    DAL requested that we clarify in paragraph (g) of the proposed AD 
which engine mount retainer (forward or aft) is to be inspected.
    We agree to clarify. We have revised paragraph (g) of this AD to 
specify the aft engine mount inner retainer.

[[Page 11793]]

Requests To Use the Airplane Maintenance Manual (AMM)

    DAL requested that we include an option for using the AMM to 
accomplish the required actions. DAL stated that paragraph (g) of the 
proposed AD specifies that the replacement must be done in accordance 
with the service information specified in paragraph (h)(1), (h)(2), or 
(h)(3) of the proposed AD. DAL recommended that operators be allowed to 
take credit for the replacement through other means such as the AMM.
    We do not agree with DAL's request. An AMM is a customized document 
that varies for each operator and depends on the airplane 
configuration. In addition, the AMM might not include all required 
compliance steps to mitigate the risk addressed in this AD. We have not 
changed this AD in this regard. However, under the provisions of 
paragraph (l) of this AD, we will consider requests for approval of 
alternative methods of compliance if sufficient data are submitted to 
substantiate that the new methods would provide an acceptable level of 
safety.

Requests To Revise Part Installation Prohibition

    DAL requested that we revise paragraph (j) of the proposed AD to 
prohibit installation of an engine mount inner retainer in lieu of 
``any part.'' DAL asserted that if not changed, paragraph (j)(l) of the 
proposed AD will prohibit the installation of all aft mounts identified 
in table 1 of Airbus Alert Operators Transmission (AOT) A71N011-15, 
Revision 01, dated February 1, 2016.
    We agree with DAL's request. We have revised paragraph (j) of this 
AD to prohibit installation of certain engine mount inner retainers.
    DAL requested that we revise paragraph (j)(3) of the proposed AD, 
which prohibits installation of parts delivered through an unidentified 
Purchase Order (PO) to provide more specific information for the 
identification of non-conforming aft engine mount inner retainers. DAL 
suggested that the proposed AD specify using the original equipment 
manufacturer (OEM) new part release certificate as a mean of verifying 
conformity for each aft engine mount inner retainer. DAL explained that 
it is suggesting this action because non-conforming field parts could 
be sold on the surplus market prior to the release of the AD under a 
non-OEM purchase order number.
    We do not agree with DAL's request to revise paragraph (j)(3) of 
the proposed AD. We have determined that paragraph (j)(3) of this AD 
clearly prohibits installation of parts delivered through an 
unidentified PO and corresponds with the MCAI. We are unaware of any 
non-conforming parts delivered through an unidentified PO that have 
been sold on the surplus market. However, if those parts exist, then 
they are prohibited from installation as of the effective date of this 
AD. We have not changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered 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 minor 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information. This service 
information describes procedures for replacement of all non-conforming 
aft engine mount retainers.
     Airbus Service Bulletin A320-71-1070, dated November 23, 
2015. This document also describes procedures for an inspection for 
non-conforming aft engine mount retainers.
     Airbus Alert Operators Transmission (AOT) A71N011-15, 
Revision 01, dated February 1, 2016. This document also contains the 
affected purchase order numbers used in identifying the affected parts.
     Goodrich Service Bulletin RA32071-165, dated October 9, 
2015. This document also contains the affected part numbers.
    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 959 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
            Action                   Labor cost         Parts cost    Cost per product   Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection...................  Up to 4 work-hours x               $0  Up to $340......  Up to $326,060.
                                $85 per hour = $340.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost            Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement........................  Up to 36 work-hours x $85           $10,000  Up to $13,060.
                                      per hour = $3,060.
----------------------------------------------------------------------------------------------------------------

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,

[[Page 11794]]

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 adding the following new airworthiness 
directive (AD):

2017-04-10 Airbus: Amendment 39-18805. Docket No. FAA-2016-6896; 
Directorate Identifier 2016-NM-016-AD.

(a) Effective Date

    This AD is effective April 3, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Airbus Model A320-211, -212, and -214 airplanes.
    (4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by a report of a production quality 
deficiency on the inner retainer installed on link assemblies of the 
aft engine mount, which could result in failure of the retainer. We 
are issuing this AD to detect and correct non-conforming retainers 
of the aft engine mount. This condition could result in loss of the 
locking feature of the nuts of the inner and outer pins; loss of the 
pins will result in the aft mount engine link no longer being 
secured to the aft engine mount, possibly resulting in damage to the 
airplane.

(f) Compliance

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

(g) Inspection and Replacement

    Within 2 months after the effective date of this AD, do an 
inspection to determine if any non-compliant aft engine mount inner 
retainer is installed; and within 2 months after the effective date 
of this AD, replace each part that meets any of the criteria 
specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Do the 
inspection in accordance with the service information specified in 
paragraph (h)(1) of this AD. Do the replacement in accordance with 
the service information specified in paragraph (h)(1), (h)(2), or 
(h)(3) of this AD. A review of airplane maintenance records is 
acceptable in lieu of the inspection required by this paragraph, if 
it can be conclusively determined that there are no non-compliant 
aft engine mount inner retainers installed on the airplane.
    (1) An aft engine mount inner retainer from an aft engine mount 
having a serial number listed in table 1 of Airbus Alert Operators 
Transmission (AOT) A71N011-15, Rev 01, dated February 1, 2016.
    (2) An aft engine mount inner retainer installed on an airplane 
between the first flight of the airplane or March 1, 2015 (whichever 
occurs later), and the effective date of this AD, and that can be 
identified by a purchase order (PO) listed in table 2 of Airbus AOT 
A71N011-15, Rev 01, dated February 1, 2016.
    (3) An aft engine mount inner retainer installed on an airplane 
between the first flight of the airplane or March 1, 2015 (whichever 
occurs later), and the effective date of this AD, and that cannot be 
identified by a PO.

(h) Service Information for Actions Required by Paragraph (g) of This 
AD

    Accomplish the replacement required by paragraph (g) of this AD 
in accordance with the service information specified in paragraph 
(h)(1), (h)(2), or (h)(3) of this AD.
    (1) The Accomplishment Instructions of Airbus Service Bulletin 
A320-71-1070, dated November 23, 2015.
    (2) Paragraph 4.2.2, ``Requirements,'' of Airbus AOT A71N011-15, 
Revision 01, dated February 1, 2016.
    (3) The Accomplishment Instructions of Goodrich Service Bulletin 
RA32071-165, dated October 9, 2015.

(i) Credit for Previous Actions

    This paragraph provides credit for the applicable actions 
required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus AOT 
A71N011-15, Revision 01, dated February 1, 2016.

(j) Parts Installation Prohibition

    As of the effective date of this AD, no person may install an 
aft engine mount retainer that meets any of the criteria specified 
in paragraph (j)(1), (j)(2), or (j)(3) of this AD on any airplane.
    (1) A part from the aft engine mount having a serial number 
listed in table 1 of Airbus AOT A71N011-15, Rev 01, dated February 
1, 2016.
    (2) A part delivered through a PO listed in table 2 of Airbus 
AOT A71N011-15, Rev 01, dated February 1, 2016.
    (3) A part delivered through an unidentified PO.

(k) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-1405; fax: 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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: For any requirement in this AD 
to obtain corrective

[[Page 11795]]

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 European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). 
If approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0010R1, dated February 16, 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-2016-6896.
    (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)(5) 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.
    (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 A320-71-1070, dated November 23, 
2015.
    (ii) Airbus Alert Operators Transmission (AOT) A71N011-15, 
Revision 01, dated February 1, 2016.
    (iii) Goodrich Service Bulletin RA32071-165, dated October 9, 
2015.
    (3) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; 
Internet: http://www.airbus.com.
    (4) For Goodrich service information identified in this AD, 
contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, 
Chula Vista, CA 91910-2098; telephone: 619-691-2719; email: 
jan.lewis@goodrich.com; Internet: http://www.goodrich.com/TechPubs.
    (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 February 7, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-03267 Filed 2-24-17; 8:45 am]
 BILLING CODE 4910-13-P


