[Federal Register Volume 74, Number 117 (Friday, June 19, 2009)]
[Rules and Regulations]
[Pages 29112-29116]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-13146]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1082; Directorate Identifier 2007-NM-337-AD; 
Amendment 39-15925; AD 2009-12-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 Airplanes; Model A300 
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and 
C4-605R Variant F Airplanes (Collectively Called A300-600 Series 
Airplanes); and Model A310 Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to the airplanes identified above. That AD 
currently requires revising the FAA-approved maintenance program to 
include a new airplane maintenance manual task that specifies a 
detailed inspection after each ram air turbine (RAT) retraction. That 
existing AD also currently requires, for certain airplanes, a one-time 
inspection to detect breaks in the bottom flange fitting of the RAT and 
corrective actions, if necessary; for certain airplanes, an adjustment 
of the ejection jack; and, for certain other airplanes, replacement of 
the aluminum part with an improved steel part. This AD also continues 
to require certain actions for additional airplanes and revising the 
FAA-approved maintenance program to include procedures for replacing 
the RAT swivel coupling fork fitting with a new steel part only. This 
AD results from a report that an additional swivel coupling of the RAT 
yoke fitting was found cracked during the accomplishment of the 
requirements of the existing AD. We are issuing this AD to prevent 
misrigging of the ejection jack of the RAT and to ensure removal of any 
RAT yoke fitting made from aluminum material. Such conditions could 
result in a broken or cracked swivel coupling and consequent failure of 
the RAT yoke fitting, which could result in the loss of RAT function 
and possible loss of critical flight control systems in the event of 
certain emergency situations.

DATES: This AD becomes effective July 24, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of July 24, 2009.

[[Page 29113]]


ADDRESSES: For service information identified in this AD, contact: 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; e-mail [email protected]; Internet http://www.airbus.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 the Document 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2007-03-09, amendment 
39-14920 (72 FR 5157, February 5, 2007). The existing AD applies to all 
Model A300 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and 
Model A310 airplanes. That NPRM was published in the Federal Register 
on October 10, 2008 (73 FR 60203). That NPRM proposed to continue to 
require revising the FAA-approved maintenance program to include a new 
airplane maintenance manual task that specifies a detailed inspection 
after each ram air turbine (RAT) retraction and, for certain airplanes, 
to continue to require replacing the aluminum yoke fitting of the 
swivel coupling of the RAT with a new steel yoke fitting. That NPRM 
also proposed to require replacing the RAT swivel coupling fork fitting 
for additional airplanes and revising the FAA-approved maintenance 
program to include procedures for replacing the RAT swivel coupling 
fork fitting with a new steel part only.

Actions Since NPRM Was Issued

    The NPRM cited Airbus Mandatory Service Bulletin A300-57-0244, 
dated March 4, 2005, as the appropriate source of service information 
for procedures to replace the RAT swivel coupling fork fitting with a 
new steel fitting. Airbus has since revised that service bulletin. 
Revision 01, dated September 3, 2007, of that service bulletin includes 
revised installation procedures. The procedures in Revision 02, dated 
November 19, 2007, of that service bulletin are essentially the same as 
those in Revision 01, dated September 3, 2007.
    We have revised paragraphs (f) and (h) of this AD to refer to 
Revision 02 of Airbus Mandatory Service Bulletin A300-57-0244. We have 
also added a new paragraph (k) to this AD to give credit for actions 
done in accordance with Revision 01 of Airbus Mandatory Service 
Bulletin A300-57-0244.
    We have also revised paragraph (f) to refer to Airbus Mandatory 
Service Bulletins A310-57-2086, Revision 01, dated September 3, 2007; 
and A300-57-6099, Revision 01, dated September 3, 2007. We referred to 
the original issue of Airbus Mandatory Service Bulletin A310-57-2086, 
dated March 1, 2005; and Airbus Mandatory Service Bulletin A300-57-
6099, dated February 23, 2005; for the replacement in paragraph (f) of 
the NPRM. The replacement procedures specified in Revision 01 of these 
service bulletins are identical to those in the original issue of these 
service bulletins.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Revise the Applicability

    Airbus requests that modification 19578 be removed from Table 1 in 
the NPRM because this modification applies to the A300F4-608ST model 
only. This model is not included on any U.S.-type certificate and is 
not referenced in paragraph (c) of the NPRM.
    We agree. Airbus Model A300F4-608ST is not included on any U.S.-
type certificate; therefore, we have removed the reference to the 
modification for this model from Table 1 of this AD.

Request for Revising Requirements

    The Air Transport Association (ATA), on behalf of its member 
American Airlines (AA), requests that paragraph (g) of the NPRM be 
revised to coincide with the requirements of paragraph (k) of the NPRM. 
AA finds that paragraphs (g) and (k) of the NPRM require similar 
actions.
    AA states that paragraph (g) of the NPRM would require changes to 
the FAA-approved maintenance program; specifically, changes to select 
AMM chapters are required, with a mandate to replace broken yoke 
fittings with new steel or aluminum parts. AA states that these AMM 
chapters are cited by both page block and date. AA states that 
paragraph (k) of the NPRM would similarly require changes to the 
maintenance program, and also would mandate changes to AMM sections; 
however, in paragraph (k) of the NPRM, specific revision dates of the 
AMM sections in question are not discussed. AA states that furthermore, 
paragraph (k) of the NPRM would require that a broken yoke be replaced 
with only a new steel part; paragraph (g) of the NPRM would authorize 
the use of an aluminum part. AA states that the requirements of 
paragraph (k) of the NPRM include the updated requirement to use only 
the steel yoke as a replacement. AA also states that paragraph (k) of 
the NPRM, unlike paragraph (g) of the NPRM, does not cite specific 
revision dates, allowing operators necessary latitude for incorporating 
future AMM revisions.
    We find that clarification is necessary. Paragraph (g) of this 
final rule restates the requirements from superseded AD 2007-03-09, and 
paragraph (l) of this final rule (referred to as paragraph (k) in the 
NPRM) provides the new requirements. Performing the actions in 
paragraph (l) of this AD terminates the requirements of paragraph (g) 
of this AD. However, the requirements of paragraph (g) of this AD must 
be retained to ensure that applicable requirements of this AD are done. 
Paragraph (g) of this final rule states that the actions must be 
accomplished in accordance with the service information; therefore that 
service information contains specific revision numbers and dates. 
Paragraph (k) provides additional information; therefore, that 
information does not contain specific dates.
    We have clarified paragraphs (g) and (l) of this AD to specify the 
actions are to be done in accordance with a method approved by the FAA 
or Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) or 
European Aviation Safety Agency (EASA). Also, we have added Notes 2 and 
4 of this final rule to specify where the information pertaining to the 
replacement and inspection procedures can be found.

[[Page 29114]]

Request for Alternative Replacement Procedures

    The ATA, on behalf of its member AA, requests that the yoke 
replacement not be limited to the accomplishment procedures contained 
in Airbus Mandatory Service Bulletin A300-57-6099. AA requests that 
alternative replacement procedures be incorporated into the final rule.
    We disagree. We find that the procedures included Airbus Mandatory 
Service Bulletin A300-57-6099 provide an adequate level of safety. 
However, we have no evidence that any alternative procedures not 
included in that service bulletin would provide an adequate level of 
safety. An operator may apply for approval of an alternative method of 
compliance (AMOC) in accordance with the procedures outlined in 
paragraph (m) of this AD. We have not changed the final rule regarding 
this issue.

Explanation of Changes to Paragraphs (g) and (l) of This AD and 
Additions of Note 2 and Note 4 in This AD

    We have revised paragraphs (g) and (l) of this AD and have added 
Note 2 and Note 4 to this AD to clarify the requirements of those 
paragraphs. The revised paragraphs (g) and (l) specify the actions are 
to be done in accordance with a method approved by the FAA. However, we 
have added Notes 2 and 4 to specify where information pertaining to the 
replacement and inspection procedures can be found. We have also moved 
Note 1 to the applicability section.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                                     Estimated Costs
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                                                                                                                          Number of U.S.-
                  Action                      Work hours     Average labor              Parts                Cost per       registered      Fleet cost
                                                             rate per hour                                   airplane        airplanes
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Replacement...............................              14             $80  $470........................          $1,590             205        $325,950
Revision of FAA-approved maintenance                     1              80  None........................              80             205          16,400
 program.
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    In consideration of the compliance time and effective date for 
accomplishing the replacement and revision of the FAA-approved 
maintenance program required by AD 2007-03-09 (retained in paragraphs 
(f) and (g) of this AD), we assume that operators of the affected 
airplanes have already initiated the required actions. The AD adds no 
new costs associated with those airplanes.

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 have 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 DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14920 (72 FR 5157, February 5, 2007) and by 
adding the following new airworthiness directive (AD):

2009-12-02 Airbus: Amendment 39-15925. Docket No. FAA-2008-1082; 
Directorate Identifier 2007-NM-337-AD.

Effective Date

    (a) This AD becomes effective July 24, 2009.

Affected ADs

    (b) This AD supersedes AD 2007-03-09.

Applicability

    (c) This AD applies to all Model A300 airplanes; Model A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and 
C4-605R Variant F airplanes; and Model A310 airplanes, certificated 
in any category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the

[[Page 29115]]

inspections described in the revisions. In this situation, to comply 
with 14 CFR 91.403(c), the operator must request approval for an 
alternative method of compliance according to paragraph (m) of this 
AD. The request should include a description of changes to the 
required inspections that will ensure the continued damage tolerance 
of the affected structure. The FAA has provided guidance for this 
determination in Advisory Circular (AC) 25-1529-1.

Unsafe Condition

    (d) This AD results from a report that an additional swivel 
coupling of the ram air turbine (RAT) yoke fitting was found cracked 
while accomplishing the requirements of the existing AD. We are 
issuing this AD to prevent misrigging of the ejection jack of the 
RAT and to ensure removal of any RAT yoke fitting made from aluminum 
material. Such conditions could result in a broken or cracked swivel 
coupling and consequent failure of the RAT yoke fitting, which could 
result in the loss of RAT function and possible loss of critical 
flight control systems in the event of certain emergency situations.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Certain Requirements of AD 2007-03-09

Replacement

    (f) For Model A300 airplanes, Model A300-600 series airplanes, 
and Model A310 airplanes equipped with Dowty Rotol RATs, except 
airplanes on which Airbus Modification 12986 has been done: Within 
12 months after March 12, 2007 (the effective date of AD 2007-03-
09), replace the RAT swivel coupling fork fitting with a new steel 
fitting, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-0244, dated March 4, 2005, or Airbus 
Mandatory Service Bulletin A300-57-0244, Revision 02, dated November 
19, 2007 (for Model A300 airplanes); Airbus Service Bulletin A300-
57-6099, dated February 23, 2005, or Airbus Mandatory Service 
Bulletin A300-57-6099, Revision 01, dated September 3, 2007 (for 
Model A300-600 series airplanes); or Airbus Service Bulletin A310-
57-2086, dated March 1, 2005, or Airbus Mandatory Service Bulletin 
A310-57-2086, Revision 01, dated September 3, 2007 (for Model A310 
airplanes); except as provided by paragraph (h) of this AD.

Revisions of FAA-Approved Maintenance Program

    (g) For all airplanes: Within 3 months after March 12, 2007, 
incorporate information into the FAA-approved maintenance program to 
specify an inspection for breaks of the bottom flange of the RAT 
swivel coupling yoke fitting after each RAT retraction; and 
replacement of the RAT swivel coupling yoke fitting with a new 
aluminum or steel part as applicable; in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (or its delegated agent); or the European 
Aviation Safety Agency (or its delegated agent). Thereafter, except 
as provided by paragraphs (l) and (m) of this AD, no alternative 
inspection intervals may be approved for the bottom flange of the 
RAT swivel coupling yoke fitting.

    Note 2: Guidance on the inspection and replacement procedures 
specified in paragraph (g) of this AD can be found in these 
documents as applicable:
     Airbus A300-600 Aircraft Maintenance Manual (AMM), 
Chapter 29-25-00, Page Block 301, dated June 1, 2005.
     Airbus A310 AMM, Chapter 29-25-00, Page Block 301, 
dated June 1, 2005.
     Airbus A300 AMM Chapter 29-25-00, Page Block 301, dated 
March 1, 2006.


    Note 3: After revising the maintenance program to include the 
required periodic inspections according to paragraph (g) or (l) of 
this AD, operators do not need to make a maintenance log entry to 
show compliance with this AD every time those inspections are 
accomplished thereafter.

New Requirements of This AD

Revised Service Bulletins

    (h) As of the effective date of this AD, use only the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-57-2086, Revision 01, dated September 3, 2007 (for Model A310 
series airplanes); Airbus Mandatory Service Bulletin A300-57-6099, 
Revision 01, dated September 3, 2007 (for Model A300-600 series 
airplanes); or Airbus Mandatory Service Bulletin A300-57-0244, 
Revision 02, dated November 19, 2007 (for Model A300 airplanes), to 
do the replacement required by paragraph (f) of this AD.

Replacement

    (i) For airplanes identified in Table 1 of this AD: Before 102 
months since first flight, or within 12 months after the effective 
date of this AD, whichever occurs later, replace the aluminum yoke 
fitting of the swivel coupling of the RAT with a new steel yoke 
fitting, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A310-57-2086, Revision 01, dated 
September 3, 2007 (for Model A310 series airplanes); or Airbus 
Mandatory Service Bulletin A300-57-6099, Revision 01, dated 
September 3, 2007 (for Model A300-600 series airplanes).

Table 1--Airplanes Affected by the Requirements of Paragraph (i) of This
                                   AD
------------------------------------------------------------------------
                                Except for those
           Model--            airplanes on which--      Or on which--
------------------------------------------------------------------------
(1) A310 series airplanes     Airbus Modification   Airbus Service
 equipped with Hamilton        12986 has been done   Bulletin
 Sundstrand RAT.               in production.        A310[dash]57[dash]2
                                                     086, dated March 1,
                                                     2005; or Airbus
                                                     Mandatory Service
                                                     Bulletin
                                                     A310[dash]57[dash]2
                                                     086, Revision 01,
                                                     dated September 3,
                                                     2007; has been done
                                                     in service.
(2) A300-600 series           Airbus Modification   Airbus Service
 airplanes equipped with       12986 has been done   Bulletin
 Hamilton Sundstrand RAT.      in production.        A300[dash]57[dash]6
                                                     099, dated February
                                                     23, 2005; or Airbus
                                                     Mandatory Service
                                                     Bulletin
                                                     A300[dash]57[dash]6
                                                     099, Revision 01,
                                                     dated September 3,
                                                     2007; has been done
                                                     in service.
------------------------------------------------------------------------

Credit for Actions Performed According to Previous Service Bulletins

    (j) Replacements done before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-57-2086, dated March 1, 
2005 (for Model A310 series airplanes); or Airbus Service Bulletin 
A300-57-6099, dated February 23, 2005 (for Model A300-600 series 
airplanes); are acceptable for compliance with the requirements of 
paragraph (i) of this AD.
    (k) Replacements done before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-57-0244, Revision 01, 
dated September 3, 2007 (for Model A300 airplanes), are acceptable 
for compliance with the requirements of paragraph (f) of this AD for 
the affected airplanes.

Revision of FAA-Approved Maintenance Program

    (l) For all airplanes: Within 3 months after the effective date 
of this AD, incorporate information into the FAA-approved 
maintenance program to specify an inspection for breaks of the 
bottom flange of the RAT swivel coupling yoke fitting after each RAT 
retraction; and replacement of the RAT swivel coupling yoke fitting 
with a new steel part; in accordance with a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or European Aviation Safety Agency (or its 
delegated agent). Thereafter, except as provided by paragraph (m) of 
this AD, no alternative inspection intervals may be approved for the 
bottom flange of the RAT swivel coupling yoke fitting. Accomplishing 
this incorporation

[[Page 29116]]

terminates the requirements of paragraph (g) of this AD.

    Note 4: Guidance on the inspection and replacement procedures 
specified in paragraph (l) of this AD can be found in these 
documents as applicable:
     Airbus A300-600 AMM, Chapter 29-25-00, Page Block 301.
     Airbus A310 AMM, Chapter 29-25-00, Page Block 301.
     Airbus A300 AMM Chapter 29-25-00, Page Block 301.

Alternative Methods of Compliance (AMOCs)

    (m) The Manager, International Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-1138; fax (425) 227-1149. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your principal maintenance inspector (PMI) or principal 
avionics inspector (PAI), as appropriate, or lacking a principal 
inspector, your local Flight Standards District Office. The AMOC 
approval letter must specifically reference this AD.

Related Information

    (n) European Aviation Safety Agency (EASA) airworthiness 
directive 2007-0273, dated October 23, 2007, and French 
airworthiness directive F-2005-089, dated June 8, 2005, also address 
the subject of this AD.

Material Incorporated by Reference

    (o) You must use the service information contained in Table 2 of 
this AD to do the actions required by this AD, as applicable, unless 
the AD specifies otherwise.

                                   Table 2--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                    Document                        Revision                           Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A300-57-0244.              02  November 19, 2007.
Airbus Mandatory Service Bulletin A300-57-6099.              01  September 3, 2007.
Airbus Mandatory Service Bulletin A310-57-2086.              01  September 3, 2007.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail [email protected]; 
Internet http://www.airbus.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on May 20, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-13146 Filed 6-18-09; 8:45 am]
BILLING CODE 4910-13-P