AD 2004-19-04

[Federal Register Volume 69, Number 180 (Friday, September 17, 2004)]
[Rules and Regulations]
[Pages 55943-55947]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20774]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-40-AD; Amendment 39-13795; AD 2004-19-04]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company 120, 140, 140A, 
150, F150, 170, 172, F172, FR172, P172D, 175, 177, 180, 182, 185, 
A185E, 190, 195, 206, P206, U206, TP206, TU206, 207, T207, 210, T210, 
336, 337, and T337 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA adopts a new airworthiness directive (AD) that will 
supersede AD 86-26-04, which applies to certain Cessna Aircraft Company 
(Cessna) 120, 140, 140A, 150, F150, 170, 172, F172, FR172, P172D, 175, 
177, 180, 182, 185, A185E, 190, 195, 205, 205A, 206, P206, P206E, 
TP206A, TU206, TU206E, U206, U206E, 207, T207, 210, T210, 336, 337, and 
T337 series airplanes. AD 86-26-04 currently requires you to inspect 
and, if necessary, modify the pilot/co-pilot upper shoulder harness 
adjusters that have certain Cessna accessory kits incorporated. This AD 
is the result of reports that additional airplanes have the same unsafe 
condition and the manufacturer revised the service information to add 
these airplanes and correct the part number of the shoulder harness 
adjusters. Consequently, this AD retains the actions of 86-26-04, adds 
additional airplanes to the applicability section of this AD, and 
incorporates the revised service information. We are issuing this AD to 
prevent slippage of the pilot/co-pilot shoulder harness, which could 
result in failure of the shoulder harness to maintain proper belt 
length adjustment and tension. Such failure could result in pilot/co-
pilot injury.

DATES: This AD becomes effective on November 1, 2004.
    As of November 1, 2004, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: You may get the service information identified in this AD 
from The Cessna Aircraft Company, Product Support P.O. Box 7706, 
Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-
9006.
    You may view the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2003-CE-40-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. 
to 4 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Gary D. Park, Aerospace Engineer, FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-
4123; facsimile: (316) 946-4107.

SUPPLEMENTARY INFORMATION:

Discussion

    What is the background of the subject matter? Cessna designed add-
on shoulder harness assembly accessory kits for the pilot/co-pilot 
seats for certain Cessna airplanes. These shoulder harness assemblies 
incorporate a retainer spring in the adjuster on the upper and lower 
shoulder harness. The retainer spring may have been inadvertently 
installed on the belt friction pin. This installation of the spring in 
the upper shoulder harness adjuster will not allow the belt webbing to 
lock in place.
    This caused us to issue AD 86-26-04, Amendment 39-5503 (52 FR 520, 
January 7, 1987). AD 86-26-04 currently requires the following on 
certain Cessna 120, 140, 140A, 150, F150, 170, 172, F172, FR172, P172D, 
175, 177, 180, 182, 185, A185E, 190, 195, 205, 205A, 206, P206, P206E, 
TP206A, TU206, TU206E, U206, U206E, 207, T207, 210, T210, 336, 337, and 
T337 series airplanes:

--Inspecting the upper shoulder harness adjuster for the presence of a 
retainer spring;
--If a retainer spring is found, removing the retainer spring; and
--Stamping out the -401 identification number.

    What has happened since AD 86-26-04 to initiate this action? We 
have received reports that additional airplanes have the same unsafe 
condition. Cessna has revised the related service information to 
include these additional airplanes.
    Cessna also revised the service information to correct the 
reference to the part number (P/N) of the shoulder harness adjusters. 
The P/N is referenced as 44030-401 in Cessna Single Engine Service 
Bulletin SEB86-8 and Cessna Multi-engine Service Bulletin MEB86-22, 
both dated November 21, 1986. The correct P/N is 443030-401.
    What is the potential impact if FAA took no action? If not 
corrected, the shoulder harness could fail to maintain proper belt 
length adjustment and

[[Page 55944]]

tension. Such failure could result in pilot/co-pilot injury.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include an AD that would apply to certain Cessna Models 120, 140, 140A, 
150, F150, 170, 172, F172, FR172, P172D, 175, 177, 180, 182, 185, 
A185E, 190, 195, 206, P206, U206, TP206, TU206, 207, T207, 210, T210, 
336, 337, and T337 series airplanes. This proposal was published in the 
Federal Register as a supplemental notice of proposed rulemaking (NPRM) 
on February 27, 2004 (69 FR 9277). The supplemental NPRM proposed to 
supersede AD 86-26-04 with a new AD that would require you to:

--Inspect the upper shoulder harness adjuster for the presence of a 
retainer spring;
--If a retainer spring is found, remove the retainer spring; and
--Stamp out the -401 identification number.
    Was the public invited to comment? The FAA encouraged interested 
persons to participate in the making of this amendment. The following 
presents the comment received on the proposal and FAA's response to the 
comment:

Comment Issue: Clarify Whether Retainer Springs, Part Number (P/N) 
443030-401, Used in Cessna Service Kits Are Affected by This AD

    What is the commenter's concern? The commenter states that there is 
confusion about whether retainer springs, P/N 443030-401, used in 
Cessna service kits are affected by this AD. The commenter states that 
the service kits are different and unrelated to the shoulder harness 
assembly accessory kits referenced in the AD. The commenter believes 
this is confusing and may result in a mechanic cutting the spring on 
the service kit adjusters in an effort to comply with this AD.
    The commenter wants us to put a note in the AD to clarify that 
Cessna service kits that incorporate the use of P/N 443030-401 are not 
affected by this AD.
    What is FAA's response to the concern? We concur with the commenter 
and will add a paragraph in the AD for clarification. We will change 
the final rule AD action based on this comment.

Conclusion

    What is FAA's final determination on this issue? We carefully 
reviewed all available information related to the subject presented 
above and determined that air safety and the public interest require 
the adoption of the rule as proposed except for the changes discussed 
above and minor editorial corrections. We have determined that these 
changes and minor corrections:

--Provide 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.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the FAA's AD system. This regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    How many airplanes does this AD impact? We estimate that this AD 
affects 75,329 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? We estimate the following costs to accomplish the 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                       Total cost
              Labor cost                         Parts cost             airplane    Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65......  No parts required............          $65  $65 x 75,329 = $4,896,385.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
modification that will be required based on the results of this 
inspection. We have no way of determining the number of airplanes that 
may need this modification:

------------------------------------------------------------------------
                                                              Total cost
             Labor cost                    Parts cost            per
                                                               airplane
------------------------------------------------------------------------
1 workhour x $65 per hour = $65....  No parts required.....          $65
------------------------------------------------------------------------

    What is the difference between the cost impact of this AD and the 
cost impact of AD 86-26-04? The difference is the addition of 26 
airplanes to the applicability section of this AD. There is no 
difference in cost to perform the inspection and the modification.

Regulatory Findings

    Will this AD impact various entities? 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.
    Will this AD involve a significant rule or regulatory action? 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); 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-CE-40-AD'' in your request.

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,

[[Page 55945]]

the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (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) 
86-26-04, Amendment 39-5503 (52 FR 520, January 7, 1987), and by adding 
a new AD to read as follows:

2004-19-04 Cessna Aircraft Company: Amendment 39-13795; Docket No. 
2003-CE-40-AD; Supersedes AD 86-26-04, Amendment 39-5503.

When Does This AD Become Effective?

    (a) This AD becomes effective on November 1, 2004.

What Other ADs Are Affected by This Action?

    (b) This AD supersedes AD 86-26-04, Amendment 39-5503.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following airplane models and serial 
numbers that are certificated in any category and incorporate one of 
the Cessna accessory kits specified in paragraph (d) of this AD.

------------------------------------------------------------------------
               Model                            Serial number
------------------------------------------------------------------------
(1) 120...........................  8000 through 15075.
(2) 140...........................  8000 through 15075.
(3) 140A..........................  15200 through 15724.
(4) 150...........................  617, 17001 through 17999, and 59001
                                     through 59018.
(5) 150A..........................  628 and 15059019 through 15059350.
(6) 150B..........................  15059351 through 15059700.
(7) 150C..........................  15059701 through 15060087.
(8) 150D..........................  15060088 through 15060772.
(9) 150E..........................  644 and 15060773 through 15061532.
(10) 150F.........................  15061533 through 15064532.
(11) 150G.........................  15064533 through 15064969 and
                                     15064971 through 15067198.
(12) 150H.........................  649 and 15067199 through 15069308.
(13) 150J.........................  15069309 through 15071128.
(14) 150K.........................  15071129 through 15072003.
(15) 170..........................  18000 through 18729.
(16) 170A.........................  18730 through 19400 and 19402
                                     through 20266.
(17) 170B.........................  20267 through 20999 and 25000
                                     through 27169.
(18) 172..........................  610, 612, 615, 28000 through 29999,
                                     36000 through 36999, and 46001
                                     through 46754.
(19) 172A.........................  622, 625, and 46755 through 47746.
(20) 172B.........................  630 and 17247747 through 17248734.
(21) 172C.........................  17248735 through 17249544.
(22) 172D.........................  17249545 through 17250572.
(23) 172E.........................  639 and 17250573 through 17251822.
(24) 172F.........................  17251823 through 17253392.
(25) 172G.........................  17253393 through 17254892.
(26) 172H.........................  638, 17254893 through 17256492, and
                                     17256494 through 17256512.
(27) 172I.........................  17256513 through 17257161.
(28) 172K.........................  17257162 through 17258486 and
                                     17258487 through 17259223.
(29) P172D........................  P17257120 through P17257188.
(30) 175..........................  626, 640, 28700A, and 55001 through
                                     56238.
(31) 175A.........................  619 and 56239 through 56777.
(32) 175B.........................  17556778 through 17557002.
(33) 175C.........................  17557003 through 17557119.
(34) 177..........................  661, 17700001, and 17700003 through
                                     17701164.
(35) 177A.........................  17701165 through 17701370.
(36) 177B.........................  17701371 through 17701471 and
                                     17701473 through 17701530.
(37) 180..........................  604, 614, 30000 through 32661.
(38) 180A.........................  32662 through 32999 and 50001
                                     through 50355.
(39) 180B.........................  50356 through 50661.
(40) 180C.........................  624 and 50662 through 50911.
(41) 180D.........................  18050912 through 18051063.
(42) 180E.........................  18051064 through 18051183.
(43) 180F.........................  18051184 through 18051312.
(44) 180G.........................  18051313 through 18051445.
(45) 180H.........................  18051446 through 18052175.
(46) 182..........................  613 and 33000 through 33842.
(47) 182A.........................  33843 through 34753, 34755 through
                                     34999, and 51001 through 51556.
(48) 182B.........................  34754, 51557 through 51622, and
                                     51624 through 52358.
(49) 182C.........................  631 and 52359 through 53007.
(50) 182D.........................  51623 and 18253008 through 18253598.
(51) 182E.........................  18253599 through 18254423.
(52) 182F.........................  18254424 through 18255058.
(53) 182G.........................  18255059 through 18255844.
(54) 182H.........................  634 and 18255846 through 18256684.
(55) 182J.........................  18256685 through 18257625.
(56) 182K.........................  18255845, 18257626 through 18257698,
                                     and 18257700 through 18258505.
(57) 182L.........................  18258506 through 18259305.
(58) 182M.........................  662, 18257699, and 18259306 through
                                     18260055.

[[Page 55946]]

 
(59) 182N.........................  18260056 through 18260445.
(60) 185..........................  632 and 185-0001 through 185-0237.
(61) 185A.........................  185-0238 through 185-0512.
(62) 185B.........................  185-0513 through 185-0653.
(63) 185C.........................  185-0654 through 185-0776.
(64) 185D.........................  185-0777 through 185-0967.
(65) 185E.........................  185-0968 through 185-1149.
(66) A185E........................  185-0968 through 185-1599 and
                                     18501600 through 18501832.
(67) 190..........................  7001 through 7999 and 16000 through
                                     16183.
(68) 195..........................  7001 through 7999 and 16000 through
                                     16183.
(69) 206..........................  206-0001 through 206-0275.
(70) P206.........................  P206-0001 through P206-0160.
(71) P206A........................  P206-0161 through P206-0306.
(72) P206B........................  P206-0307 through P206-0419.
(73) P206C........................  P206-0420 through P206-0519.
(74) P206D........................  P206-0520 through P206-0603.
(75) P206E........................  P20600604 through P20600647.
(76) U206.........................  U206-0276 through U206-0437.
(77) U206A........................  U206-0438 through U206-0656.
(78) U206B........................  U206-0657 through U206-0914.
(79) U206C........................  U206-0915 through U206-1234.
(80) U206D........................  U206-1235 through U206-1444 and
                                     U20601445 through U20601587.
(81) TP206A.......................  P206-0161 through P206-0306.
(82) TP206B.......................  P206-0307 through P206-0419.
(83) TP206C.......................  P206-0420 through P206-0519.
(84) TP206D.......................  P206-0520 through P206-0603.
(85) TP206E.......................  P20600604 through P20600647.
(86) TU206A.......................  U206-0487 through U206-0656.
(87) TU206B.......................  U206-0657 through U206-0914.
(88) TU206C.......................  U206-0915 through U206-1234.
(89) TU206D.......................  U206-1235 through U206-1444 and
                                     U20601445 through U20601587.
(90) 207..........................  20700001 through 20700190.
(91) T207.........................  20700001 through 20700190.
(92) 210..........................  618 and 57001 through 57575.
(93) 210-5 (205)..................  641, 648, and 205-0001 through 205-
                                     0480.
(94) 210-5 (205A).................  205-0481 through 205-0577.
(95) 210A.........................  616 and 21057576 through 21057840.
(96) 210B.........................  21057841 through 21058085.
(97) 210C.........................  21058086 through 21058139 and
                                     21058141 through 21058220.
(98) 210D.........................  21058221 through 21058510.
(99) 210E.........................  21058511 through 21058715.
(100) 210F........................  21058716 through 21058818.
(101) 210G........................  21058819 through 21058936.
(102) 210H........................  21058937 through 21059061.
(103) 210J........................  21059062 through 21059199.
(104) 210K........................  21059200 through 21059351.
(105) T210F.......................  T210-0001 through T210-0197.
(106) T210G.......................  T210-0198 through T210-0307.
(107) T210H.......................  T210-0308 through T210-0392.
(108) T210J.......................  T210-0393 through T210-0454.
(109) T210K.......................  21059200 through 21059351.
(110) F150G.......................  F150-0068 through F150-0219.
(111) F150H.......................  F150-0220 through F150-0389.
(112) F150J.......................  F150-0390 through F150-0529.
(113) F150K.......................  F15000530 through F15000658.
(114) F172D.......................  F172-0001 through F172-0018.
(115) F172E.......................  F172-0019 through F172-0085.
(116) F172F.......................  F172-0086 through F172-0179.
(117) F172G.......................  F172-0180 through F172-0319.
(118) F172H.......................  F172-0320 through F172-0654 and
                                     F17200655 through F17200754.
(119) FR172E......................  FR17200001 through FR17200060.
(120) FR172F......................  FR17200061 through FR17200145.
(121) FR172G......................  FR17200146 through FR17200225.
(122) 336.........................  633, 636, and 336-0001 through 336-
                                     0195.
(123) 337.........................  647 and 337-0002 through 337-0239.
(124) 337A........................  337-0240 through 337-0305, 337-0307
                                     through 337-0469, and 337-0471
                                     through 337-0525.
(125) 337B........................  656, 337-0001, 337-0470, 337-0526
                                     through 337-0568, and 337-0570
                                     through 337-0755.
(126) 337C........................  337-0756 through 337-0978.
(127) 337D........................  337-0979 through 337-1193.
(128) 337E........................  33701194 through 33701316.
(129) T337B.......................  337-0001, 337-0470, 337-0526 through
                                     337-0568, and 37-0570 through 337-
                                     0755.
(130) T337C.......................  337-0756 through 337-0978.
(131) T337D.......................  337-0979 through 337-1193.
(132) T337E.......................  33701194 through 33701316.
------------------------------------------------------------------------


[[Page 55947]]

What Cessna Accessory Kits Are Affected by This AD?

    (d) The following is a list of the affected Cessna accessory 
kits:

                          Cessna Accessory Kit
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
AK140-10
AK150-7
AK150-121
AK170-10
AK177-10
AK182-75
AK195-10
AK210-77
AK210-93
AK210-171
AK210-172
AK210-173
AK210-174
AK336-32
AK336-36
AK336-103
------------------------------------------------------------------------


    Note: Retainer springs, part number (P/N) 443030-401, used in 
Cessna service kits are not affected by this AD.

What Is the Unsafe Condition Presented in This AD?

    (e) The actions specified in this AD are intended to prevent 
slippage of the pilot/co-pilot shoulder harness, which could result 
in failure of the shoulder harness to maintain proper belt length 
adjustment and tension. This failure could result in pilot/co-pilot 
injury.

What Must I Do To Address This Problem?

    (f) To address this problem, you must do the following:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Inspect only the upper        Within the next 25  Follow Cessna
 shoulder harness adjuster (part   hours time-in-      Single Engine
 number (P/N) 443030-401) for      service (TIS)       Service Bulletin
 the presence of a retainer        after November 1,   SEB86-8, Revision
 spring.                           2004 (the           1, and Cessna
                                   effective date of   Multi-engine
                                   this AD).           Service Bulletin
                                                       MEB86-22,
                                                       Revision 1, both
                                                       dated July 28,
                                                       2003.
(2) If a retainer spring is       Prior to further    Follow Cessna
 found during the inspection of    flight after the    Single Engine
 the upper shoulder harness        inspection          Service Bulletin
 adjuster (P/N 443030-401)         required in         SEB86-8, Revision
 required in paragraph (f)(1) of   paragraph (f)(1)    1, and Cessna
 this AD: (i) Remove the spring    of this AD.         Multi-engine
 by cutting each side; and (ii)                        Service Bulletin
 stamp out the -401                                    MEB86-22,
 identification number.                                Revision 1, both
                                                       dated July 28,
                                                       2003.
(3) If a retainer spring is not   Prior to further    Follow Cessna
 found during the inspection of    flight after the    Single Engine
 the upper shoulder harness        inspection          Service Bulletin
 adjuster (P/N 443030-401)         required in         SEB86-8, Revision
 required in paragraph (f)(1) of   paragraph (f)(1)    1, and Cessna
 this AD, make an entry in the     of this AD.         Multi-engine
 airplane log book showing                             Service Bulletin
 compliance with this AD.                              MEB86-22,
                                                       Revision 1, both
                                                       dated July 28,
                                                       2003.
(4) Only incorporate Cessna       As of November 1,   Follow Cessna
 Accessory Kits identified in      2004 (the           Single Engine
 paragraph (d) of this AD that     effective date of   Service Bulletin
 have been inspected and           this AD).           SEB86-8, Revision
 modified in accordance with                           1, and Cessna
 paragraphs (f)(1), (f)(2),                            Multi-engine
 (f)(2)(i), and (f)(2)(ii) of                          Service bulletin
 this AD.                                              MEB86-22,
                                                       Revision 1, both
                                                       dated July 28,
                                                       2003.
------------------------------------------------------------------------

    (g) If you did the actions of this AD using Cessna Single Engine 
Service Bulletin SEB86-8 and Cessna Multi-engine Service Bulletin 
MEB86-22, both dated November 21, 1986, no further action is 
required as long as you used shoulder harness adjuster, P/N 443030-
401.

May I Request an Alternative Method of Compliance?

    (h) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Wichita Aircraft 
Certification Office (ACO), FAA. For information on any already 
approved alternative methods of compliance, contact Gary D. Park, 
Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 
Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 
67209; telephone: (316) 946-4123; facsimile: (316) 946-4107.

Does This AD Incorporate Any Material by Reference?

    (i) You must do the actions required by this AD following the 
instructions in Cessna Single Engine Service Bulletin SEB86-8, 
Revision 1, and Cessna Multi-engine Service Bulletin MEB86-22, 
Revision 1, both dated July 28, 2003. The Director of the Federal 
Register approved the incorporation by reference of this service 
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You 
may get a copy from Cessna Aircraft Company, Product Support, P.O. 
Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; 
facsimile: (316) 942-9006. You may review copies at FAA, Central 
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas 
City, Missouri 64106; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    Issued in Kansas City, Missouri, on September 8, 2004.
Dorenda D. Baker,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-20774 Filed 9-16-04; 8:45 am]
BILLING CODE 4910-13-P