**FEDERAL AVIATION ADMINISTRATION**

**AIRWORTHINESS DIRECTIVES**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS,**

**BALLOONS, & AIRSHIPS**

**BIWEEKLY 2002-16**

This electronic copy may be printed and used in lieu of the FAA biweekly
paper copy.

U.S. Department of Transportation

Federal Aviation Administration

Regulatory Support Division

Delegation and Airworthiness Programs Branch, AIR-140

P. O. Box 26460

Oklahoma City, OK 73125-0460

FAX 405-954-4104

Biweekly 2002-01

  ------------ ---------- ----------------- ----------------------------------
  2001-26-13              Pilatus Aircraft  PC-7

  2001-26-25              Grob-Werke        Sailplane: G102 Club Astir III,
                                            G102 Club Astir IIIb, and G102
                                            Standard Astir III

  2002-01-02              Turbomeca S.A.    Engine: Arrius 1A
  ------------ ---------- ----------------- ----------------------------------

Biweekly 2002-02

+--------+---------+----------------+---------------------------------+
| 2000   | C, S    | Eurocopter     | Rotorcraft: AS-350B, BA, B1,    |
| -20-19 | 86-     | France         | B2, B3, C, D, and D1, and       |
|        | 15-10R2 |                |                                 |
|        |         |                | AS-355E, F, F1, F2 and N        |
+--------+---------+----------------+---------------------------------+
| 2001   | FR      | MD Helicopters | Rotorcraft: MD900               |
| -25-51 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2001   | FR      | Eurocopter     | Rotorcraft: EC135               |
| -26-52 |         | Deutschland    |                                 |
+--------+---------+----------------+---------------------------------+
| 2001   | FR      | Eurocopter     | Rotorcraft: AS350B, B1, B2, B3, |
| -26-53 |         | France         | BA, D, and AS355E               |
+--------+---------+----------------+---------------------------------+
| 2002   |         | British        | HP.137 Jetstream Mk.1,          |
| -01-05 |         | Aerospace      | Jetstream Series 200, Jetstream |
|        |         |                | Series 3101, and Jetstream      |
|        |         |                | Model 3201                      |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Eurocopter     | Rotorcraft: AS332L2             |
| -01-06 |         | France         |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Bell           | Rotorcraft: 430                 |
| -01-07 |         | Helicopter     |                                 |
|        |         | Textron Canada |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Pilatus        | PC-7, PC-12, and PC-12/45       |
| -01-09 |         | Aircraft       |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Raytheon       | 65-90, 65-A90, B90, C90, C90A,  |
| -01-10 |         | Aircraft       | 65-A90-1, 65-A90-4, E90, and    |
|        |         |                | H-90                            |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Pilatus        | BN-2, BN-2A, BN-2A-2, BN-2A-3,  |
| -01-11 |         | Britten-Norman | BN-2A-6, BN-2A-8,               |
|        |         |                |                                 |
|        |         |                | BN-2A-9, BN-2A-20, BN-2A-21,    |
|        |         |                | BN-2A-26, BN-2A-27,             |
|        |         |                |                                 |
|        |         |                | BN-2B-20, BN-2B-21, BN-2B-26,   |
|        |         |                | BN-2B-27, BN-2T, BN-2T-4R,      |
|        |         |                |                                 |
|        |         |                | BN2A MK. III, BN2A MK. III-2,   |
|        |         |                | and BN2A MK. III-3              |
+--------+---------+----------------+---------------------------------+

**Biweekly 2002-03**

+--------+---------+----------------+---------------------------------+
| 2001   |         | Honeywell      | Engine: LTS101-600A-2,          |
| -25-04 |         | International  | LTS101-600A-3, LTP101-600A-1A,  |
|        |         |                | LTP101-700A-1A Turboprop        |
+--------+---------+----------------+---------------------------------+
| 2001   | FR      | Eurocopter     | Rotorcraft: EC 155B             |
| -26-54 |         | France         |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Fairchild      | SA26-AT, SA226-AT, SA226-T,     |
| -01-16 | 8       | Aircraft       | SA226-T(B), SA226-TC, SA227-AC, |
|        | 6-24-11 |                | SA227-AT, SA227-TT              |
|        | &       |                |                                 |
|        |         |                |                                 |
|        | 8       |                |                                 |
|        | 6-25-04 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Eurocopter     | Rotorcraft: SE 3130, SE 313B,   |
| -01-30 |         | France         | SA 315B, SE 3160, SA 316B,      |
|        |         |                | SA 316C, SA 3180, SA 318B, SA   |
|        |         |                | 318C, and SA 319B               |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Bell           | Rotorcraft: HH-1K, TH-1F,       |
| -01-31 | 200     | Helicopter     | TH-1L, UH-1A, UH-1B, UH-1E,     |
|        | 0-22-51 |                | UH‑1F, UH-1H, UH-1L, and UH-1P, |
|        |         |                | SW204, SW204HP, SW205, and      |
|        |         |                | SW205A-1                        |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Eagle Aircraft | 150B                            |
| -02-01 |         | PTY            |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | E       | Eurocopter     | Rotorcraft: AS350B, AS350BA,    |
| -02-51 |         | France         | AS350B1, AS350B2, AS350B3,      |
|        |         |                | AS350C, AS350D, AS350D1,        |
|        |         |                | AS355E, AS355F, AS355F1,        |
|        |         |                | AS355F2, AS355N, and EC130 B4   |
+--------+---------+----------------+---------------------------------+
| 2002   | E, S    | Eurocopter     | Rotorcraft: AS350B, AS350BA,    |
| -03-52 | 200     | France         | AS350B1, AS350B2, AS350B3,      |
|        | 2-02-51 |                | AS350C, AS350D, AS350D1,        |
|        |         |                | AS355E, AS355F, AS355F1,        |
|        |         |                | AS355F2, AS335N, and EC130 B4   |
+--------+---------+----------------+---------------------------------+

**Biweekly 2002-04**

  ------------ ---------- ----------------- ----------------------------------
  2001-26-55   FR         Eurocopter France Rotorcraft: AS350B, AS350B1,
                                            AS350B2, AS350BA, AS350B3, AS350C,
                                            AS350D, AS350D1, AS355E, AS355F,
                                            AS355F1, AS355F2, and AS355N

  2002-02-10              Pilatus Britten   BN-2, BN-2A, BN-2A-2, BN-2A-3,
                          Norman            BN-2A-6, BN-2A-8, BN-2A-9,
                                            BN-2A-20, BN-2A-21, BN-2A-26,
                                            BN-2A-27, BN-2B-20, BN-2B-21,
                                            BN-2B-26, BN-2B-27, BN-2T, and
                                            BN-2T-4R

  2002-02-11              Pilatus Britten   BN-2, BN-2A, BN-2A-2, BN-2A-3,
                          Norman            BN-2A-6, BN-2A-8, BN-2A-9,
                                            BN-2A-20, BN-2A-21, BN-2A-26,
                                            BN-2A-27, BN-2B-20, BN-2B-21,
                                            BN-2B-26, BN-2B-27, BN-2T,
                                            BN-2T-4R, BN2A MK.III, BN2A
                                            MK.III-2, and BN2A MK.III-3

  2002-03-01              Honeywell         Engine: T5311A, T5311B, T5313B,
                          International     T5317A, T5317B, and former
                                            military T53-L-11, T53-L-11A,
                                            T53-L-11B, T53-L-11C, T53-L-11D,
                                            T53-L-11A S/SA, T53-L-13B,
                                            T53-L-13B S/SA, T53-L-13B S/SB,
                                            and T53-L-703 Turboshaft

  2002-03-02   S 98-13-03 British Aerospace HP.137 Jetstream Mk.1, Jetstream
                                            Series 200, Jetstream Series 3101
  ------------ ---------- ----------------- ----------------------------------

Biweekly 2002-04 continued

  ------------ ------------ ----------------- ----------------------------------
  2002-03-03                Socata-Groupe     TBM 700
                            Aerospatiale      

  2002-03-04                Pilatus Britten   BN-2, BN-2A, BN-2A-2, BN-2A-3,
                            Norman            BN-2A-6, BN-2A-8, BN-2A-9,
                                              BN-2A-20, BN-2A-21, BN-2A-26,
                                              BN-2A-27, BN-2B-20, BN-2B-21,
                                              BN-2B-26, BN-2B-27, BN-2T,
                                              BN-2T-4R, BN2A MK.III, BN2A
                                              MK.III-2, and BN2A MK.III-3

  2002-03-09                Honeywell         Engine: LTS101 Series Turboshaft
                            International     and LTP101 Series Turboprop

  2002-03-16   S 2000-18-52 Bell Helicopters  OH-13E, OH-13H, and OH-13S
                            (See AD)          

  2002-04-51   E            Textron Lycoming  Engine: LTIO-540 and TIO-540 (See
                                              AD)
  ------------ ------------ ----------------- ----------------------------------

Biweekly 2002-05

  ------------ ---------- ----------------- ----------------------------------
  2002-04-07              Eurocopter France Rotorcraft: AS350BA and B2

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

Biweekly 2002-06

+--------+---------+----------------+---------------------------------+
| 2002   | R1      | Honeywell      | Engine: LTS101 Series           |
| -03-09 |         | International  | Turboshaft and LTP101 Series    |
|        |         |                | Turboprop                       |
+--------+---------+----------------+---------------------------------+
| 2002   | FR, S   | Eurocopter     | Rotorcraft: AS350B, AS350BA,    |
| -03-52 | 200     | France         | AS350B1, AS350B2, AS350B3,      |
|        | 2-02-51 |                | AS350C, AS350D, AS350D1,        |
|        |         |                | AS355E, AS355F, AS355F1,        |
|        |         |                | AS355F2, AS355N, and EC130 B4   |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Socata-Groupe  | MS 892A-150, MS 892E-150, MS    |
| -05-04 | 7       | Aerospatiale   | 893A, MS 893E, MS 894A, MS      |
|        | 7-15-06 |                | 894E, Rallye 150T, and Rallye   |
|        |         |                | 150ST                           |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Cirrus Design  | SR20 and SR22                   |
| -05-05 |         | Corporation    |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | COR, S  | Sikorsky       | Rotorcraft: S-76A               |
| -05-06 | 8       | Aircraft       |                                 |
|        | 6-09-11 | Corporation    |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Eurocopter     | Rotorcraft: AS350B, AS350B1,    |
| -06-04 |         | France         | AS350B2, AS350B3, AS350BA,      |
|        |         |                | AS350C, AS350D, AS350D1,        |
|        |         |                | AS355E, AS355F, AS355F1,        |
|        |         |                | AS355F2, and AS355N             |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Transport      | Appliance: Mode C 621A-3 Air    |
| -06-05 |         | Category       | Traffic Control (ATC)           |
|        |         | Airplanes      | Transponder(s)                  |
|        |         |                |                                 |
|        |         | Rockwell       |                                 |
|        |         | Collins        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Rolls-Royce    | Engine: 250-C28, -C28B, and     |
| -06-08 |         | Corp.          | -C28C                           |
+--------+---------+----------------+---------------------------------+
| 2002   | E, S    | Bell           | Rotorcraft: 407                 |
| -06-52 | 200     | Helicopter     |                                 |
|        | 0-02-12 | Textron Canada |                                 |
+--------+---------+----------------+---------------------------------+

Biweekly 2002-07

  ------------ ---------- ----------------- ----------------------------------
  2002-06-06              Rockwell Collins, Appliance: TDR-94 and TDR-94D Mode
                          Inc.              S Transponders

  2002-06-10              Pilatus Aircraft  PC-12 and PC-12/45

  2002-07-01              Cessna            P206C, TP206C, P206D, TP206D,
                                            P206E, TP206E, U206C, TU206C,
                                            U206D, TU206D, U206E, TU206E,
                                            U206F, TU206F, U206G, TU206G, 207,
                                            T207, 207A, T207A, 210G, 210H,
                                            210J, 210K, T210K, 210L, T210L,
                                            210M, T210M, 210N, T210N, P210N,
                                            T210G, T210H, T210J
  ------------ ---------- ----------------- ----------------------------------

Biweekly 2002-08

  ------------ ------------ ----------------- ----------------------------------
  2001-24-51   FR           MD Helicopters,   Rotorcraft: 600N
                            Inc.              

  2002-06-52   FR, S        Bell Helicopter   Rotorcraft: 407
               2000-02-12   Textron Canada    

  2002-08-01                Fairchild         SA226-AT, SA226-T, SA226-T(B),
                            Aircraft, Inc.    SA226-TC, SA227-AC, SA227-AT, and
                                              SA227-TT

  2002-08-02   S 2001-20-14 Fairchild         SA226-AT, SA226-T, SA226-T(B),
                            Aircraft, Inc.    SA226-TC, SA227-AC, SA227-AT,
                                              SA227-TT, and SA227-TT(300)

  2002-08-03   S 2001-22-01 Enstrom           Rotorcraft: F-28, F-28A, F-28C,
                            Helicopter Corp.  F-28F, 280, 280C, 280F and 280FX
  ------------ ------------ ----------------- ----------------------------------

Biweekly 2002-09

+--------+---------+----------------+---------------------------------+
| 2001   | FR, S   | Schweizer      | Rotorcraft: 269A, 269A-1, 269B, |
| -25-52 | 7       | Aircraft Corp. | 269C, and TH-55A                |
|        | 6-18-01 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | FR,     | Eurocopter     | Rotorcraft: AS350B, AS350BA,    |
| -03-52 | COR, S  | France         | AS350B1, AS350B2, AS350B3,      |
|        | 200     |                | AS350C, AS350D, AS350D1,        |
|        | 2-02-51 |                | AS355E, AS355F, AS355F1,        |
|        |         |                | AS355F2, AS355N, and EC130 B4   |
+--------+---------+----------------+---------------------------------+
| 2002   | COR,    | Fairchild      | SA226-AT, SA226-T, SA226-T(B),  |
| -08-02 |         | Aircraft, Inc. | SA226-TC, SA227-AC, SA227-AT,   |
|        | S       |                | SA227-TT, and SA227-TT(300)     |
|        | 200     |                |                                 |
|        | 1-20-14 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Piaggio Aero   | P-180                           |
| -08-04 |         | Industries     |                                 |
|        |         | S.p.A.         |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Eurocopter     | Rotorcraft: SA341G, SA342J, and |
| -08-16 | 200     | France         | SA-360C                         |
|        | 1-19-51 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | E       | Bell           | Rotorcraft: 205A, A-1 and B     |
| -08-53 |         | Helicopter     |                                 |
|        |         | Textron, Inc.  |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | E       | Bell           | Rotorcraft: 222, 222B, 222U,    |
| -08-54 |         | Helicopter     | and 230                         |
|        |         | Textron Canada |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Eurocopter     | Rotorcraft: AS332L2             |
| -09-03 |         | France         |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Bell           | 205A, 205A-1, 205B, 212, 412,   |
| -09-04 |         | Helicopter     | 412EP, and 412CF                |
|        |         | Textron, Inc.  |                                 |
+--------+---------+----------------+---------------------------------+
|        |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| **Bi   |         |                |                                 |
| weekly |         |                |                                 |
| 200    |         |                |                                 |
| 2-10** |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Hartzell       | Propellers: ( )HC-( )( )Y( )-(  |
| -09-08 | 7       | Propellers     | )( )( ) Compact Series          |
|        | 7-12-06 |                |                                 |
|        | R2      |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Honeywell      | Engine: T53 Series              |
| -09-09 |         | International  |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | COR,    | SOCATA         | TBM 700                         |
| -09-11 |         |                |                                 |
|        | S       |                |                                 |
|        | 200     |                |                                 |
|        | 1-05-03 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | COR     | Raytheon       | C90A                            |
| -09-12 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Cessna         | 441                             |
| -09-13 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | E, S    | Bell           | Rotorcraft: 204B, 205A, A-1,    |
| -09-51 | 200     | Helicopters    | and B                           |
|        | 2-08-53 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | MD Helicopters | Rotorcraft: MD-900              |
| -10-05 | 200     |                |                                 |
|        | 1-07-09 |                |                                 |
+--------+---------+----------------+---------------------------------+

  ------------ ---------- ------------------ ----------------------------------
  **Biweekly                                 
  2002-11**                                  

  2002-10-13              Raytheon Aircraft  58P, 60, A60, B60, and 65-88
                          Company            

  2002-10-14              Bombardier-Rotax   Engine: 914 F Series
                          GmbH               

  2002-11-01              Eurocopter         Rotorcraft: EC135
                          Deutschland        

  2002-11-02              Raytheon Aircraft  390
                          Company            

  2002-11-05              Air Tractor, Inc.  AT-400, AT-401, AT-401B, AT-402,
                                             AT-402A, AT-402B, AT-501, AT-802,
                                             and AT-802A
  ------------ ---------- ------------------ ----------------------------------

**Biweekly 2002-12**

  ------------ ------------ ----------------- ----------------------------------
  2002-11-03                Air Tractor, Inc. AT-502, AT-502A, AT-502B, AT-503A

  2002-11-07                Raytheon Aircraft E55, E55A, A56TC, 58, 58A, 58P,
                                              58PA, 58TC, and 58TCA

  2002-11-09                Bell Helicopter   Rotorcraft: 407

  2002-11-10   S 2001-25-08 Sikorsky          Rotorcraft: S-70A, S-70C

  2002-12-02                Eurocopter France Rotorcraft: AS332L2

  2002-12-03                Eurocopter France Rotorcraft: AS332L2
  ------------ ------------ ----------------- ----------------------------------

**Biweekly 2002-13**

  ------------ ------------ ----------------- ----------------------------------
  2002-11-03   COR          Air Tractor, Inc. AT-502, AT-502A, AT-502B, AT-503A

  2002-12-07   S 2000-18-53 Textron Lycoming  Engine: O--320--H1AD, --H1BD,
                                              --H2AD, --H2BD, --H3AD, ‑H3BD,
                                              (L)O--360,--A1AD, --A1F6D,
                                              --A1G6D, --A1LD, --A3AD, --A4AD,
                                              --A5AD, --E1A6D, IO--360--A1B6D,
                                              --A1D6D, --A3B6D, --A3D6D,
                                              --C1E6D, --J1AD, --J1A6D,
                                              (L)TO--360,--A1A6D, ‑C1A6D,
                                              --E1A6D, --F1A6D, TIO--360--C1A6D,
                                              (L)HIO‑360‑E1AD, --E1BD, --F1AD,
                                              O--540--H1A5D, --H1B5D, ‑H2A5D,
                                              --H2B5D, --J1A5D, --J1B5D,
                                              --J1C5D, --J1D5D, ‑J2A5D, --J2B5D,
                                              --J2C5D, --J2D5D, --J3A5D,
                                              --J3C5D, --L3C5D, IO‑540‑C4D5D,
                                              --K1A5D, --K1B5D, --K1E5D,
                                              --K1F5D, ‑K1G5D, --K1J5D, --L1A5D,
                                              ‑L1B5D, --M1A5D, --M1B5D, --M2A5D,
                                              ‑T4A5D, --T4B5D, --T4C5D, --U1A5D,
                                              ‑U1B5D, --V4A5D, ‑W1A5D, --W3A5D,
                                              (L)TIO--540--K1AD, --S1AD,
                                              --AA1AD, ‑AB1AD, --AB1BD, --F2BD,
                                              --J2BD, --N2BD, ‑R2AD, --T2AD,
                                              ‑V2AD, AEIO--540--L1B5D,
                                              TIO--541--E Series,
                                              TIGO--541--D1A, --D1B, --E1A,
                                              IO--720--A1BD, --B1BD, --C1BD,
                                              --D1BD, --D1CD

  2002-12-09                Honeywell         Engine: TPE331-11U, -12B, -12JR,
                            International     -12UA, -12UAR, and ‑12UHR Series
                                              Turboprop

  2002-12-14   S 99-23-07   Eurocopter France Rotorcraft: SA330F, G, SA330J,
                                              AS332C, L, and L1

  2002-13-04   S 2000-11-51 Teledyne          Engine: C-125, C145, O-300,
                            Continental       IO-360, TSIO-360, and LTSIO-520-AE
                                              Series Reciprocating

  2002-13-05                MD Helicopters    Rotorcraft: 369D, 369E, 369F, and
                                              369FF

  2002-13-06                Eurocopter        Rotorcraft: BO-105A, BO-105C,
                            Deutschland       BO-105 C-2, BO-105 CB-2, BO-105
                                              CB-4, BO-105S, BO-105 CS-2, BO-105
                                              CBS-2, BO-105 CBS-4, and BO-105LS
                                              A-1

  2002-13-51   E            Bell Helicopters  Rotorcraft: HH‑1K, TH‑1F, TH‑1L,
                                              UH‑1A, UH‑1B, UH‑1E, UH‑1F, UH‑1H,
                                              UH‑1L, UH‑1P; SW204, SW204HP,
                                              SW205, and SW205A‑1
  ------------ ------------ ----------------- ----------------------------------

**Biweekly 2002-14**

  ------------ ---------- ----------------- ----------------------------------
  2002-13-02              Air Tractor       AT-300, AT-301, AT-302, and
                                            AT-400A

  2002-13-07              Honeywell, Inc.   Appliance: Inertial Reference Unit

  2002-13-08              de Havilland      DHC-2 Mk.I, DHC-2 Mk. II, and
                                            DHC-2 Mk. III

  2002-13-11              Eurocopter France Rotorcraft: EC120B

  2002-14-01              Eurocopter France Rotorcraft: AS332L and AS332L1

  2002-14-17   S 99-12-01 Eurocopter        Rotorcraft: EC135
                          Deutschland       

  2002-14-18              Glaser-Dirks      Sailplane: DG-400 and DG-800A
                          Flugzeugbau       

  2002-14-51   E          Agusta S.p.A      Rotorcraft: A109E and A119
  ------------ ---------- ----------------- ----------------------------------

**Biweekly 2002-15**

+--------+---------+----------------+---------------------------------+
| 2002   | COR     | Teledyne       | Engine: C-125, C145, O-300,     |
| -13-04 |         | Continental    | IO-360, TSIO-360, and           |
|        | S       |                | LTSIO-520-AE Series             |
|        | 200     |                | Reciprocating                   |
|        | 0-11-51 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Rockwell       | Appliance: Air Data Computers   |
| -14-19 |         | Collins        | (ADC)                           |
+--------+---------+----------------+---------------------------------+
| 2002   | COR     | Pilatus        | PC-12 and PC-12/45              |
| -14-22 |         | Aircraft       |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Turbomeca S.A. | Engine: Arriel Models 1A, 1A1,  |
| -14-26 |         |                | 1B, 1D, and 1D1 Turboshaft      |
+--------+---------+----------------+---------------------------------+
| 2002   |         | de Havilland   | DHC-2, Mk. I, DHC-2 Mk. II, and |
| -14-28 |         |                | DHC-2 Mk. III                   |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Diamond        | Sailplane: H-36 \'\'Dimona\'\', |
| -15-01 |         | Aircraft       | HK 36 R \'\'Super Dimona\'\',   |
|        |         |                | HK 36 TC, HK 36 TS, HK 36 TTC,  |
|        |         |                | HK 36 TTC-ECO, HK 36 TTC-ECO    |
|        |         |                | (Restricted Category), and HK   |
|        |         |                | 36 TTS                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Hamilton       | Appliance: Auxiliary Power      |
| -15-02 |         | Sundstrand     | Units (APU\'s)                  |
|        |         | Power Sys.     |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | E       | Sikorsky       | Rotorcraft: S76A, B, and C      |
| -15-51 |         |                |                                 |
+--------+---------+----------------+---------------------------------+

**Biweekly 2002-16**

  ------------ ------------ ----------------- ----------------------------------
  2002-08-54   FR           Bell Helicopter   Rotorcraft: 222, 222B, 222U, 230

  2002-09-51   FR, S        Bell Helicopter   Rotorcraft: 204B, 205A, A-1, and B
               2002-08-53                     

  2002-13-51   FR           Bell Helicopter,  Rotorcraft: HH-1K, TH-1F, TH-1L,
                            (See AD)          UH-1A, UH-1B, UH-1E, UH-1F, UH-1H,
                                              UH-1L, and UH-1P; SW204, SW204HP,
                                              SW205, and SW205A-1

  2002-15-04                Honeywell         Engine: T5313B, T5317 Series, and
                            International     former military T53 Series
                                              Turboshaft

  2002-15-05                Turbomeca         Engine: Makila 1 A, 1 A1, and 1 A2
                                              Turboshaft

  2002-15-06                Air Tractor       AT-802 and AT-802A

  2002-15-07                MD Helicopters    Rotorcraft: MD900

  2002-15-08                Eurocopter France Rotorcraft: EC120B, EC155B,
                                              SA330F, SA330G, SA330J, AS332C,
                                              AS332L, AS332L1, AS332L2, AS350B,
                                              AS350BA, AS350B1, AS350B2,
                                              AS350B3, AS350D, AS355E, AS355F,
                                              AS355F1, AS355F2, AS355N,
                                              AS-365N2, AS 365 N3, SA-365N, and
                                              SA-365N1
  ------------ ------------ ----------------- ----------------------------------

**BW 2002-16**

**BELL HELICOPTER TEXTRON CANADA**

**AIRWORTHINESS DIRECTIVE**

**FINAL RULE**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS**

**2002-08-54 Bell Helicopter Textron Canada:** Amendment 39-12835,
Docket No. 2002-SW-22-AD.

**Applicability:** The following model helicopters with the listed part
number (P/N) installed, certificated in any category:

  ------------ ---------------------------- -------------------- --------------------
  **Model**    **With hub assembly P/N**    **With grip assembly **With pitch horn
                                            P/N**                assembly P/N**

  \(1\) 222 or 222--011--101--103, -105,    222--010--104--105   222--011--104--101
  222B         -107, or -109                                     

               222--012--101--103, or -107  222--012--104--101   222--012--102--101

  \(2\) 222U   222--011--101--105, -107, or 222--010--104--105   222--011--104--101
               -109                                              

               222--012--101--103, OR -107  222--012--104--101   222--012--102--101

  \(3\) 230    222--012--101--105, or -109  222--012--104--101   222--012--102--101
  ------------ ---------------------------- -------------------- --------------------

**Note 1:** This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For helicopters that have been modified,
altered, or repaired so that the performance of the requirements of this
AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (d) of
this AD. The request should include an assessment of the effect of the
modification, alteration, or repair on the unsafe condition addressed by
this AD; and if the unsafe condition has not been eliminated, the
request should include specific proposed actions to address it.

**Compliance:** Required as indicated, unless accomplished previously.

To prevent failure of the grip or pitch horn and subsequent loss of
control of the helicopter, if either the grip or pitch horn has
accumulated 1250 or more hours time-in-service (TIS) since initial
installation on any helicopter, accomplish the following:

\(a\) Before further flight and thereafter at intervals not to exceed 8
hours TIS:

\(1\) Wipe clean the main rotor grip and pitch horn surfaces to remove
grease and dirt in the check area as shown in Figure 1 of this AD:

![](media/image2.png){width="6.797916666666667in"
height="8.275694444444444in"}

\(2\) Visually check both main rotor grips for a crack, paying
particular attention to the inboard and outboard tangs/portions of the
grip, which are in direct contact with the pitch horns and the main
rotor blades. Check the area to at least 3 inches beyond the grip/pitch
and grip/blade contact areas as shown in Figure 2 of this AD:

![](media/image3.png){width="4.395138888888889in" height="6.2in"}

\(3\) Visually check all visible portions of each pitch horn for a
crack. Pay particular attention to the attachment lugs of the pitch
horns, which are in direct contact with the inboard tangs of the main
rotor grips, as shown in Figure 3 of this AD, and the four large bolt
cutouts, as shown in Figure 4 of this AD:

![](media/image4.png){width="5.704861111111111in" height="5.8in"}

![](media/image5.png){width="4.876388888888889in" height="6.8in"}

\(4\) An owner/operator (pilot) may perform the visual check required by
this AD. The pilot must enter compliance with paragraph (a) of this AD
into the helicopter maintenance records in accordance with 14 CFR 43.11
and 91.417(a)(2)(v)). A pilot may perform this check because it involves
only a visual check for a crack in the grip or pitch horn and can be
performed equally well by a pilot or a mechanic.

\(b\) Within 7 days or 10 hours TIS, whichever occurs first, and
thereafter at intervals not to exceed 25 hours TIS, using a 10-power or
higher magnifying glass, visually inspect each grip and pitch horn for a
crack in accordance with the Accomplishment Instructions, Part II,
paragraphs 1 and 2, of Bell Helicopter Textron Alert Service Bulletin
Nos. 222U-02-64, 222-02-93, and 230-02-26, all dated April 1, 2002, as
applicable.

\(c\) If a crack is found, replace the unairworthy grip or pitch horn
with an airworthy part before further flight.

\(d\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Regulations Group, FAA. Operators shall
submit their requests through an FAA Principal Maintenance Inspector,
who may concur or comment and then send it to the Manager, Regulations
Group.

**Note 2:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
Regulations Group.

\(e\) Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
inspection requirements of paragraph (b) of this AD can be accomplished.

\(f\) The inspection shall be done in accordance with the Accomplishment
Instructions, Part II, paragraphs 1 and 2, of Bell Helicopter Textron
Alert Service Bulletin Nos. 222U-02-64, 222-02-93, and 230-02-26, all
dated April 1, 2002, as applicable. This incorporation by reference was
approved by the Director of the Federal Register in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Bell
Helicopter Textron Canada, 12,800 Rue de l\'Avenir, Mirabel, Quebec
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272.
Copies may be inspected at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at
the Office of the Federal Register, 800 North Capitol Street, NE., suite
700, Washington, DC.

\(g\) This amendment becomes effective on August 21, 2002, to all
persons except those persons to whom it was made immediately effective
by Emergency AD 2002-08-54, issued May 2, 2002, which contained the
requirements of this amendment.

**Note 3:** The subject of this AD is addressed in Transport Canada
(Canada) AD CF-2002-23, dated April 2, 2002.

**FOR FURTHER INFORMATION CONTACT:** Charles Harrison, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort
Worth, Texas 76193-0110, telephone (817) 222-5128, fax (817) 222-5961.

Issued in Fort Worth, Texas, on July 25, 2002.

Eric Bries,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02-19486 Filed 8-5-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-16**

**BELL HELICOPTER TEXTRON, INC**

**AIRWORTHINESS DIRECTIVE**

**FINAL RULE**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS**

**2002-09-51 Bell Helicopter Textron, Inc.:** Amendment 39-12839. Docket
No. 2002-SW-24-AD. Supersedes Emergency AD 2002-08-53, Docket No.
2002-SW-23-AD.

**Applicability:** Model 204B, 205A, A-1, and B helicopters, with tail
rotor (T/R) grip, part number (P/N) 205-011-711-101, installed,
certificated in any category.

**Note 1:** This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For helicopters that have been modified,
altered, or repaired so that the performance of the requirements of this
AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (c) of
this AD. The request should include an assessment of the effect of the
modification, alteration, or repair on the unsafe condition addressed by
this AD; and if the unsafe condition has not been eliminated, the
request should include specific proposed actions to address it.

**Compliance:** Required before further flight, unless accomplished
previously.

To prevent failure of the T/R grip and subsequent loss of helicopter
control, accomplish the following:

\(a\) Clean the T/R grip.

\(b\) Determine if the T/R grip is made of steel by placing a magnet on
the exterior of the main body of the T/R grip. Do not make this
determination by placing the magnet on the steel bushing or steel
interior liner. If the main body of the T/R grip is not made of steel,
replace it with an airworthy steel T/R grip. Only replacement T/R grips
made of steel are eligible for installation.

\(c\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Rotorcraft Certification Office, FAA.
Operators shall submit their requests through an FAA Principal
Maintenance Inspector, who may concur or comment and then send it to the
Manager, Rotorcraft Certification Office.

\(d\) Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
requirements of this AD can be accomplished.

\(e\) This amendment becomes effective on August 22, 2002, to all
persons except those persons to whom it was made immediately effective
by Emergency AD 2002-09-51, issued May 9, 2002, which contained the
requirements of this amendment.

**FOR FURTHER INFORMATION CONTACT:** Kennedy Jones, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5148, fax (817)
222-5783.

Issued in Fort Worth, Texas, on July 26, 2002.

Eric Bries,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02-19875 Filed 8-6-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-16**

**BELL HELICOPTER**

**AIRWORTHINESS DIRECTIVE**

**FINAL RULE**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS**

**2002-13-51 Arrow Falcon Exporters, Inc. (previously Utah State
University); Firefly Aviation Helicopter Services (previously Erickson
Air-Crane Co.); Garlick Helicopters, Inc.; Global Helicopter Technology,
Inc.; Hagglund Helicopters, LLC (previously Western International
Aviation, Inc.); Hawkins and Powers Aviation, Inc.; International
Helicopters, Inc.; Robinson Air Crane, Inc.; Smith Helicopters; Southern
Helicopter, Inc.; Southwest Florida Aviation; Tamarack Helicopters, Inc.
(previously Ranger Helicopters Services, Inc.); U.S. Helicopter, Inc.;
and Williams Helicopter Corporation (previously Scott Paper Co.):**
Amendment 39-12836. Docket No. 2002-SW-21-AD.

**Applicability:** Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E,
UH-1F, UH-1H, UH-1L, and UH-1P; Southwest Florida Aviation SW204,
SW204HP, SW205, and SW205A-1 helicopters manufactured by Bell Helicopter
Textron, Inc. for the Armed Forces of the United States, with tail rotor
(T/R) grip, part number 205-011-711-101, installed, certificated in any
category.

**Note 1:** This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For helicopters that have been modified,
altered, or repaired so that the performance of the requirements of this
AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (c) of
this AD. The request should include an assessment of the effect of the
modification, alteration, or repair on the unsafe condition addressed by
this AD; and if the unsafe condition has not been eliminated, the
request should include specific proposed actions to address it.

**Compliance:** Required before further flight, unless accomplished
previously.

To prevent failure of the T/R grip and subsequent loss of control of the
helicopter, accomplish the following:

\(a\) Clean the T/R grip.

\(b\) Determine if the T/R grip is made of steel by placing a magnet on
the exterior of the main body of the T/R grip. Do not make this
determination by placing the magnet on the steel bushing or steel
interior liner. If the main body of the T/R grip is not made of steel,
replace it with an airworthy steel T/R grip. Only replacement T/R grips
made of steel are eligible for installation.

\(c\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Rotorcraft Certification Office, FAA.
Operators shall submit their requests through an FAA Principal
Maintenance Inspector, who may concur or comment and then send it to the
Manager, Rotorcraft Certification Office.

**Note 2:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
Rotorcraft Certification Office.

\(d\) Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
requirements of this AD can be accomplished.

\(e\) This amendment becomes effective on August 19, 2002, to all
persons except those persons to whom it was made immediately effective
by Emergency AD 2002-13-51, issued June 27, 2002, which contained the
requirements of this amendment.

**FOR FURTHER INFORMATION CONTACT:** Kennedy Jones, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5148, fax (817)
222-5783.

Issued in Fort Worth, Texas, on July 25, 2002.

Eric Bries,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02-19489 Filed 8-1-02; 8:45 am\]

BILLING CODE 4910-13-U

**BW 2002-16**

**HONEYWELL INTERNATIONAL, INC.,**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS**

**2002-15-04 Honeywell International, Inc., (formerly AlliedSignal, Inc.
and Textron Lycoming) T5313B, T5317 Series, and T53 Series Turboshaft
Engines:** Amendment 39-12832. Docket No. 2000-NE-32-AD.

**Applicability:** This airworthiness directive (AD) is applicable to
Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron
Lycoming) T5313B series, T5317 series, and former military T53 series,
turboshaft engines with centrifugal compressor impellers having serial
numbers (SN\'s) 83317, 83327, 83328, or 83330 installed. These engines
are installed on, but not limited to Bell Helicopter Textron 204, 205,
and 209 series, and Kaman K-1200 series helicopters, and the following
surplus military helicopters that have been certified in accordance with
§§21.25 or 21.27 of the Federal Aviation Regulations (14 CFR 21.25 or
21.27): Bell Helicopter Textron manufactured AH-1, UH-1, and SW-204/205
(UH-1) series.

**Note 1:** This AD applies to each engine identified in the preceding
applicability provision, regardless of whether it has been modified,
altered, or repaired in the area subject to the requirements of this AD.
For engines that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (i) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD; and,
if the unsafe condition has not been eliminated, the request should
include specific proposed actions to address it.

**Compliance:** Compliance with this AD is required as indicated, unless
already done.

To prevent premature failure of the impellers from being operated beyond
their design service life, which could result in an uncontained engine
failure, in-flight shutdown, or damage to the helicopter, do the
following:

**Life Limits**

\(a\) When conducting a revised centrifugal compressor impeller
operating cycle count on impellers having SN\'s 83317, 83327, 83328, or
83330, consider these impellers to be centrifugal compressor impeller
P/N 1-100-078-07. The life limit must use the value as if these
centrifugal compressor impellers are P/N 1-100-078-07.

**Revised Operating Cycle Count (Prorate) for T53 Engines**

\(b\) For T5313B series, T5317 series, and former military T53 series
engines, within 25 operating cycles or 7 calendar days, whichever occurs
first, after the effective date of this AD, perform the following:

\(1\) Conduct a revised centrifugal compressor impeller operating cycle
count (prorate) in accordance with paragraph 2.E.of the Honeywell
International, Inc. Service Bulletin (SB) that applies to the engine,
from the following list:

\(i\) For T53-L-13B series engines, use SB T53-L-13B-0020, Revision 3,
dated October 25, 2001.

\(ii\) For T53-L-13B/D engines, use SB T53-L-13B/D-0020, Revision 1,
dated April 25, 2001.

\(iii\) For T53-L-703 engines, use SB T53-L-703-0020, Revision 1, dated
April 25, 2001.

\(iv\) For T5313B series and T5317 series engines, use SB T531B/17-0020,
Revision 6, dated May 2, 2001.

\(2\) Remove from service centrifugal compressor impellers with SN\'s
83317, 83327, 83328, or 83330, that exceed their new life limit as
calculated in accordance with paragraph (b)(1) of this AD.

**Impeller Marking**

\(c\) At the next access to the centrifugal compressor impeller, mark
the impeller by vibropeening a line over the -14 suffix, and vibropeen a
-07 suffix immediately following the -14. Use the following vibropeening
parameters:

\(1\) Vibropeen to a depth of 0.001-0.006 inch.

\(2\) Do not vibropeen within 0.30 inch of corners, fillets, or sharp
edges.

**Definition**

\(d\) For the purpose of this AD, access to the centrifugal compressor
impeller is defined as whenever the turboshaft engine is disassembled
sufficiently as specified by the applicable maintenance manual, to
expose the compressor impeller for marking in accordance with paragraph
(c) of this AD.

**Inspection of Impellers on T5313B and T5317 Series Engines**

\(e\) For T5313B and T5317 series engines, inspect centrifugal
compressor impellers having SN\'s 83317, 83327, 83328, or 83330, for
cracks in accordance with the Accomplishment Instructions of Textron
Lycoming SB No. T5313B/17-0052, Revision 2, dated December 16, 1993, as
follows:

\(1\) For those centrifugal compressor impellers installed on
AlliedSignal, Inc. Model T5313B engines, accomplish the following:

\(i\) For centrifugal compressor impellers with equal to or greater than
4,600 cycles in service (CIS) on the effective date of this AD,
initially inspect within 200 CIS after the effective date of this AD.

\(ii\) For those centrifugal compressor impellers with less than 4,600
CIS on the effective date of this AD, initially inspect no later than
4,800 CIS.

\(2\) For those centrifugal compressor impellers installed on
AlliedSignal, Inc. T5317 series engines, accomplish the following:

\(i\) For those centrifugal compressor impellers with equal to or
greater than 3,500 CIS on the effective date of this AD, initially
inspect within 200 CIS after the effective date of this AD.

\(ii\) For those centrifugal compressor impellers with less than 3,500
CIS on the effective date of this AD, initially inspect no later than
3,700 CIS.

\(3\) Centrifugal compressor impellers found cracked in accordance with
the Accomplishment Instructions of Textron Lycoming SB No.
T5313B/17-0052, Revision 2, dated December 16, 1993, must be removed
from service and replaced with a serviceable part that does not exceed
the life limit.

\(4\) If no cracks are detected, perform repetitive inspections of the
centrifugal compressor impellers at intervals not to exceed 500 CIS
since last inspection in accordance with the Accomplishment Instructions
of Textron Lycoming SB No. T5313B/17-0052, Revision 2, dated December
16, 1993.

**Inspection of Impellers on T53-L-13B Series Engines**

\(f\) For T53-L-13B series engines with centrifugal compressor impellers
having SN\'s 83317, 83327, 83328, or 83330, perform the following:

\(1\) Within 25 operating hours from the effective date of this AD,
inspect the centrifugal compressor impeller for cracks using the revised
cycle count (prorate) required by paragraph (b)(1) of this AD, in
accordance with Accomplishment Instructions of AlliedSignal, Inc. SB No.
T53-L-13B-0108, Revision 1, dated November 22, 1999.

\(2\) If cracks are detected, then prior to further flight, replace
centrifugal compressor impellers found cracked in accordance with the
Accomplishment Instructions of AlliedSignal, Inc. SB No. T53-L-13B-0108,
Revision 1, dated November 22, 1999, and replace with a centrifugal
compressor impeller P/N 1-100-078-13/-14.

\(3\) If no cracks are detected, perform repetitive inspections of the
centrifugal compressor impellers at intervals not to exceed 100
operating hours since last inspection in accordance with the
Accomplishment Instructions of AlliedSignal, Inc. SB No. T53-L-13B-0108,
Revision 1, dated November 22, 1999.

\(4\) Within 300 operating hours or 6 calendar months, whichever occurs
first, after the effective date of this AD, replace centrifugal
compressor impellers having SN\'s 83317, 83327, 83328, or 83330, with a
centrifugal compressor impeller P/N 1-100-078-13/-14. Replacement of
centrifugal compressor impellers having SN\'s 83317, 83327, 83328, or
83330, with a centrifugal compressor impeller P/N 1-100-078-13/-14
constitutes terminating action for the inspection requirements of
paragraphs (f)(1) and (f)(3) of this AD.

**Inspection of Impellers on T53-L-13B/D Series Engines**

\(g\) For T53-L-13B/D series engines with centrifugal compressor
impellers having SN\'s 83317, 83327, 83328, or 83330, perform the
following:

\(1\) Within 25 operating hours from the effective date of this AD,
inspect the centrifugal compressor impeller for cracks using the revised
cycle count (prorate) required by paragraph (b)(1) of this AD, in
accordance with Accomplishment Instructions of AlliedSignal, Inc. SB No.
T53-L-13B/D-0108, Revision 1, dated November 22, 1999.

\(2\) If cracks are detected, then prior to further flight, replace
centrifugal compressor impellers found cracked in accordance with the
Accomplishment Instructions of AlliedSignal, Inc. SB No.
T53-L-13B/D-0108, Revision 1, dated November 22, 1999, and replace with
a centrifugal compressor impeller P/N 1-100-078-13/-14.

\(3\) If no cracks are detected, perform repetitive inspections of the
centrifugal compressor impellers at intervals not to exceed 100
operating hours since last inspection in accordance with the
Accomplishment Instructions of AlliedSignal, Inc. SB No.
T53-L-13B/D-0108, Revision 1, dated November 22, 1999.

\(4\) Within 300 operating hours or 6 calendar months, whichever occurs
first, after the effective date of this AD, replace centrifugal
compressor impellers having SN\'s 83317, 83327, 83328, or 83330, with a
centrifugal compressor impeller P/N 1-100-078-13/-14. Replacement of
centrifugal compressor impellers having SN\'s 83317, 83327, 83328, or
83330, with a centrifugal compressor impeller P/N 1-100-078-13/-14
constitutes terminating action for the inspection requirements of
paragraphs (g)(1) and (g)(3) of this AD.

**Inspection of Impellers on T53-L-703 Engines**

\(h\) For T53-L-703 series engines with centrifugal compressor impellers
having SN\'s 83317, 83327, 83328, or 83330, perform the following:

\(1\) Within 25 operating hours from the effective date of this AD,
inspect the centrifugal compressor impeller for cracks using the revised
cycle count (prorate) required by paragraph (b)(1) of this AD, in
accordance with Accomplishment Instructions of AlliedSignal, Inc. SB No.
T53-L-703-0108, Revision 1, dated November 22, 1999.

\(2\) If cracks are detected, then prior to further flight, replace
centrifugal compressor impellers found cracked in accordance with the
Accomplishment Instructions of AlliedSignal, Inc. SB No. T53-L-703-0108,
Revision 1, dated November 22, 1999, and replace with a centrifugal
compressor impeller part number (P/N) 1-100-078-13/-14.

\(3\) If no cracks are detected, perform repetitive inspections of the
centrifugal compressor impellers at intervals not to exceed 100
operating hours since last inspection in accordance with the
Accomplishment Instructions of AlliedSignal, Inc. SB No. T53-L-703-0108,
Revision 1, dated November 22, 1999.

\(4\) Within 300 operating hours or 6 calendar months, whichever occurs
first, after the effective date of this AD, replace centrifugal
compressor impellers having SN\'s 83317, 83327, 83328, or 83330, with a
centrifugal compressor impeller P/N 1-100-078-13/-14. Replacement of
centrifugal compressor impellers having SN\'s 83317, 83327, 83328, or
83330, with a centrifugal compressor impeller P/N 1-100-078-13/-14
constitutes terminating action for the inspection requirements of
paragraphs (h)(1) and (h)(3) of this AD.

**Alternative Methods of Compliance**

\(i\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Los Angeles Aircraft Certification Office
(ACO). Operators must submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send it
to the Manager, Los Angeles ACO.

**Note 2:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(j\) Special flight permits may be issued in accordance with §§21.197
and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) to operate the helicopter to a location where the requirements
of this AD can be done.

**Documents That Have Been Incorporated by Reference**

\(k\) The inspections must be done in accordance with the following
SB\'s:

+----------------------------------------+--------+-------+-----------+
| **Document No.**                       | **P    | **    | **Date**  |
|                                        | ages** | Revis |           |
|                                        |        | ion** |           |
+----------------------------------------+--------+-------+-----------+
| Honeywell International, Inc., SB      | All    | 6     | May 2,    |
| T5313B/17--0020                        |        |       | 2001.     |
|                                        |        |       |           |
| Total pages 14                         |        |       |           |
+----------------------------------------+--------+-------+-----------+
| Honeywell International, Inc., SB      | All    | 3     | Oct. 25,  |
| T53--L--13B--0020                      |        |       | 2001.     |
|                                        |        |       |           |
| Total pages 13                         |        |       |           |
+----------------------------------------+--------+-------+-----------+
| Honeywell International, Inc., SB      | All    | 1     | April 25, |
| T53--L--13B/D--0020                    |        |       | 2001.     |
|                                        |        |       |           |
| Total pages 12                         |        |       |           |
+----------------------------------------+--------+-------+-----------+
| Honeywell International, Inc., SB      | All    | 1     | April 25, |
| T53--L--703--0020                      |        |       | 2001.     |
|                                        |        |       |           |
| Total pages 12                         |        |       |           |
+----------------------------------------+--------+-------+-----------+

+----------------------------------------+--------+-------+-----------+
| Textron Lycoming SB, SB                | All    | 2     | Dec. 16,  |
| T5313B/17--0052                        |        |       | 1993.     |
|                                        |        |       |           |
| Total pages 8                          |        |       |           |
+----------------------------------------+--------+-------+-----------+
| AlliedSignal, Inc., SB                 | 1      | Ori   | July 22,  |
| T53--L--13B--0108                      |        | ginal | 1999.     |
|                                        |        |       |           |
| Total pages 12                         |        |       |           |
+----------------------------------------+--------+-------+-----------+
|                                        | 2      | 1     | Nov. 22,  |
|                                        |        |       | 1999.     |
+----------------------------------------+--------+-------+-----------+
|                                        | 3--12  | Ori   | July 22,  |
|                                        |        | ginal | 1999.     |
+----------------------------------------+--------+-------+-----------+
| Allied Signal, Inc., SB                | 1      | Ori   | July 22,  |
| T53--L--13B/D--0108                    |        | ginal | 1999.     |
|                                        |        |       |           |
| Total pages 12                         |        |       |           |
+----------------------------------------+--------+-------+-----------+
|                                        | 2      | 1     | Nov. 22,  |
|                                        |        |       | 1999.     |
+----------------------------------------+--------+-------+-----------+
|                                        | 3--12  | Ori   | July 22,  |
|                                        |        | ginal | 1999.     |
+----------------------------------------+--------+-------+-----------+
| AlliedSignal, Inc., SB                 | 1      | Ori   | July 22,  |
| T53--L--703--0108                      |        | ginal | 1999.     |
|                                        |        |       |           |
| Total pages 12                         |        |       |           |
+----------------------------------------+--------+-------+-----------+
|                                        | 2      | 1     | Nov. 22,  |
|                                        |        |       | 1999.     |
+----------------------------------------+--------+-------+-----------+
|                                        | 3--12  | Ori   | July 22,  |
|                                        |        | ginal | 1999.     |
+----------------------------------------+--------+-------+-----------+

This incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Copies may be obtained from Honeywell International Inc. Aerospace
Services Attn.: Data Distribution, M/S 64-3/2101-201, PO Box 29003,
Phoenix, AZ 85038-9003; telephone (602) 365-2493, fax (602) 365-5577.
Copies may be inspected, by appointment, at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA; or at the Office of the Federal Register, 800 North
Capitol Street, NW, suite 700, Washington, DC.

**Effective Date**

\(l\) This amendment becomes effective on September 10, 2002.

**FOR FURTHER INFORMATION CONTACT:** Robert Baitoo, Aerospace Engineer,
Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone:
(562) 627-5245; fax: (562) 627-5210.

Issued in Burlington, Massachusetts, on July 19, 2002.

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

\[FR Doc. 02-19253 Filed 8-5-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-16**

**TURBOMECA**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS**

**2002-15-05 Turbomeca:** Amendment 39-12833. Docket No. 2001-NE-23-AD.

**Applicability**

This airworthiness directive (AD) is applicable to Turbomeca Makila 1 A,
1 A1, and 1 A2 turboshaft engines with digital electronic control units
(DECU\'s) and electronic control units (ECU\'s) that have a part number
(P/N) listed in the following Table 1:

  ---------------------------------------------------- ------------------
  **TABLE 1.---ECU AND DECU P/N'S**                    

  **ECU or DECU P/N**                                  **Used on**

  0 177 69 810 0, 0 177 69 811 0, 0 177 69 812 0, 0    Makila 1 A and 1
  177 69 813 0, 0 177 69 814 0, 0 177 69 815 0, 0 177, A1 engines.
  69 816 0, 0 177 69 817 0, 0 177 69 818 0, 0 177 69   
  819 0, 0 177 69 820 0, 0 177 69 824 0, 0 177 69, 825 
  0, 0 177 69 826 0, 0 177 69 827 0, 0 177 69 828 0,   
  and 0 177 69 829 0.                                  

  70CMB01040                                           Makila 1 A2
                                                       engines.
  ---------------------------------------------------- ------------------

These engines are installed on, but not limited to Eurocopter France
model AS 332C, AS 332L, AS 332L1 and AS 332L2, helicopters.

**Note 1:** This AD applies to each engine identified in the preceding
applicability provision, regardless of whether it has been modified,
altered, or repaired in the area subject to the requirements of this AD.
For engines that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (c) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD; and,
if the unsafe condition has not been eliminated, the request should
include specific proposed actions to address it.

**Compliance**

Compliance with this AD is required within 45 days after the effective
date of this AD, unless already done.

To prevent an engine overspeed condition resulting from the failure of
two or more NTL channels, do the following:

\(a\) For Makila 1 A and 1 A1 engines do either of the following:

\(1\) Replace ECU\'s that have a P/N listed in Table 1 of this AD, with
ECU\'s that have been modified to modification standard TU 215, or

\(2\) Replace the comparator / selector circuit board in accordance with
Turbomeca service bulletin (SB) 298 73 0166, dated October 5, 2001.

\(b\) For Makila 1 A2 engines, replace DECU, P/N 70CMB01040, with
modified DECU, P/N 70CMB01050. Information on the modified DECU may be
found in Turbomeca service bulletin (SB) 298 73 0149, dated January 13,
2000.

**Alternative Methods of Compliance**

\(c\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Engine Certification Office (ECO). Operators
must submit their request through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, ECO.

**Note 2:** Information concerning the existence of approved alternative
methods of compliance with this airworthiness directive, if any, may be
obtained from the ECO.

**Special Flight Permits**

\(d\) Special flight permits may be issued in accordance with Secs.
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) to operate the helicopter to a location where the requirements
of this AD can be done.

**Documents That Have Been Incorporated By Reference**

\(e\) The inspection must be done in accordance with Turbomeca Service
Bulletin No. 298 73 0166, dated October 5, 2001. This incorporation by
reference was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from Turbomeca, 40220 Tarnos, France. Copies may be inspected
at the FAA, New England Region, Office of the Regional Counsel, 12 New
England Executive Park, Burlington, MA; or at the Office of the Federal
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

**Note 3:** The subject of this AD is addressed in DGAC airworthiness
directives 2000-068(A), dated February 9, 2000, and 2001-546(A), dated
November 14, 2001.

**Effective Date**

\(f\) This amendment becomes effective on August 16, 2002.

**FOR FURTHER INFORMATION CONTACT:** Glorianne Niebuhr, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7132; fax (781) 238-7199.

Issued in Burlington, Massachusetts, on July 23, 2002.

Francis A. Favara,

Acting Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

\[FR Doc. 02-19164 Filed 7-31-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-16**

**AIR TRACTOR, INC.:**

**AIRWORTHINESS DIRECTIVE**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS**

**2002-15-06 Air Tractor, Inc.:** Amendment 39-12834; Docket No.
2000-CE-76-AD.

\(a\) *What airplanes are affected by this AD?* This AD affects Models
AT-802 and AT-802A airplanes, serial numbers 802-0001 through 802-0081,
that are certificated in any category.

\(b\) *Who must comply with this AD?* Anyone who wishes to operate any
of the airplanes identified in paragraph (a) of this AD must comply with
this AD.

\(c\) *What problem does this AD address?* The actions specified by this
AD are intended to prevent the rudder control cable from breaking
because of the rudder control cables wearing in the fairlead area.
Broken rudder control cables could result in loss of rudder control.

\(d\) *What actions must I accomplish to address this problem?* To
address this problem, you must accomplish the following:

  ------------------------ ------------------- ---------------------------
  **Actions**              **Compliance**      **Procedures**

  \(1\) Replace the rudder Within the next 500 Accomplish the replacements
  control cables and       hours               in accordance with Snow
  fairlead with part       time-in-service     Engineering Company Service
  numbers 70524--10--500   (TIS) after         Letter #199, dated May 30,
  or 70524--6--500, and    September 13, 2002  2000, and the applicable
  70122--1, as specified   (the effective date drawing number 70523 of the
  in the service letter.   of this AD), unless replacement kit, as
                           already             specified in the service
                           accomplished.       letter.

  \(2\) Do not install any As of September 13, Not Applicable.
  rudder control cable     2002 (the effective 
  that does not have a     date of this AD).   
  stainless steel sleeve                       
  crimped to the cable in                      
  the fairlead area.                           
  ------------------------ ------------------- ---------------------------

\(e\) *Can I comply with this AD in any other way?* You may use an
alternative method of compliance or adjust the compliance time if:

\(1\) Your alternative method of compliance provides an equivalent level
of safety; and

\(2\) The Manager, Fort Worth Airplane Certification Office (ACO),
approves your alternative. Submit your request through an FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Fort Worth ACO.

**Note:** This AD applies to each airplane identified in paragraph (a)
of this AD, regardless of whether it has been modified, altered, or
repaired in the area subject to the requirements of this AD. For
airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD; and,
if you have not eliminated the unsafe condition, specific actions you
propose to address it.

\(f\) *Where can I get information about any already-approved
alternative methods of compliance?* Contact Garry D. Sills, Aerospace
Engineer, FAA, Fort Worth Airplane Certification Office, 2601 Meacham
Boulevard, Fort Worth, Texas 76193-0150; telephone: (817) 222-5154;
facsimile: (817) 222-5960.

\(g\) *What if I need to fly the airplane to another location to comply
with this AD?* The FAA can issue a special flight permit under sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) to operate your airplane to a location where you can accomplish
the requirements of this AD.

\(h\) *Are any service bulletins incorporated into this AD by
reference?* Actions required by this AD must be done in accordance with
Snow Engineering Company Service Letter \# 199, dated May 30, 2000. The
Director of the Federal Register approved this incorporation by
reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may get copies
from Air Tractor, Inc., PO Box 485, Olney, Texas 76374. You may view
copies at the FAA, Central Region, Office of the Regional Counsel, 901
Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal
Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.

\(i\) *When does this amendment become effective?* This amendment
becomes effective on September 13, 2002.

**FOR FURTHER INFORMATION CONTACT:** Garry D. Sills, Aerospace Engineer,
FAA, Fort Worth Airplane Certification Office, 2601 Meacham Boulevard,
Fort Worth, Texas 76193-0150; telephone: (817) 222-5154; facsimile:
(817) 222-5960.

Issued in Kansas City, Missouri, on July 24, 2002.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02-19257 Filed 7-31-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-16**

**MD HELICOPTERS, INC.**

**AIRWORTHINESS DIRECTIVE**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS**

**2002-15-07 MD Helicopters, Inc.:** Amendment 39-12837. Docket No.
2001-SW-25-AD.

**Applicability:** Model MD900 helicopters, serial number (S/N)
900-00008, 900-00010 through 900-00098, and 900-00100, with a
lateral-mixer bellcrank assembly (bellcrank), part number (P/N)
900C2010203-105, installed, certificated in any category.

**Note 1:** This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For helicopters that have been modified,
altered, or repaired so that the performance of the requirements of this
AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (e) of
this AD. The request should include an assessment of the effect of the
modification, alteration, or repair on the unsafe condition addressed by
this AD; and if the unsafe condition has not been eliminated, the
request should include specific proposed actions to address it.

**Compliance:** Before further flight, unless accomplished previously.

To prevent fatigue failure of the bellcrank and subsequent loss of
lateral control of the helicopter, accomplish the following:

\(a\) Create a component history card or equivalent record for each
bellcrank and record the hours time-in-service (TIS) of the bellcrank.
If the hours TIS of the bellcrank cannot be determined, use the
helicopter\'s total hours TIS as the hours TIS for the bellcrank.

\(b\) Apply a S/N to the bellcrank in accordance with the Accomplishment
Instructions, paragraph (1)(a) and (1)(b), of MD Helicopters, Inc.
Service Bulletin SB 900-084, dated December 3, 2001.

\(c\) Remove any bellcrank that has exceeded 13,300 hours TIS.

\(d\) This AD revises the Limitations section of the maintenance manual
by establishing a life limit of 13,300 hours TIS for bellcrank, P/N
900C2010203-105.

\(e\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Los Angeles Aircraft Certification Office
(LAACO), FAA. Operators shall submit their requests through an FAA
Principal Maintenance Inspector, who may concur or comment and then send
it to the Manager, LAACO.

**Note 2:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
LAACO.

\(f\) Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
requirements of this AD can be accomplished.

\(g\) The marking of the S/N shall be done in accordance with the
Accomplishment Instructions, paragraphs (1)(a) and (1)(b), of MD
Helicopters, Inc. Service Bulletin SB 900-084, dated December 3, 2001.
This incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Copies may be obtained from MD Helicopters Inc., Attn: Customer Support
Division, 4555 E. McDowell Rd., Mail Stop M615-GO48, Mesa, Arizona
85215-9734, telephone 1-800-388-3378, fax 480-891-6782, or on the Web at
[http://www.mdhelicopters.com](http://www.mdhelicopters.com/). Copies
may be inspected at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.

\(h\) This amendment becomes effective on September 10, 2002.

**FOR FURTHER INFORMATION CONTACT:** Jon Mowery, Aviation Safety
Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe
Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone
(562) 627-5322, fax (562) 627-5210.

Issued in Fort Worth, Texas, on July 24, 2002.

Eric Bries,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02-19487 Filed 8-5-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-16**

**EUROCOPTER FRANCE**

**AIRWORTHINESS DIRECTIVE**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS**

**2002-15-08 Eurocopter France:** Amendment 39-12838. Docket No.
2001-SW-50-AD.

**Applicability:** Model EC120B, EC155B, SA330F, SA330G, SA330J, AS332C,
AS332L, AS332L1, AS332L2, AS350B, AS350BA, AS350B1, AS350B2, AS350B3,
AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS-365N2, AS 365 N3,
SA-365N, and SA-365N1 helicopters, with a SIREN load release unit (cargo
hook), part number (P/N) AS21-5-1 through -7, and a cargo hook serial
number less than 415, installed, certificated in any category.

**Note 1:** This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in the area subject to the
requirements of this AD. For helicopters that have been modified,
altered, or repaired so that the performance of the requirements of this
AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (b) of
this AD. The request should include an assessment of the effect of the
modification, alteration, or repair on the unsafe condition addressed by
this AD; and if the unsafe condition has not been eliminated, the
request should include specific proposed actions to address it.

**Compliance:** Required before the next flight utilizing the cargo
hook, unless accomplished previously.

To prevent failure of a cargo hook, inability to release a load creating
an additional hazard in an emergency situation, and subsequent loss of
control of a helicopter, accomplish the following:

\(a\) With the cargo hook in the no-load position, measure the clearance
\'\'J\'\' in accordance with Figure 1 of this AD. Remove any cargo hook
if clearance \'\'J\'\' is equal to or greater than 14 millimeters (0.55
inches). See Figure 1:

![](media/image6.png){width="3.7291666666666665in"
height="5.308333333333334in"}

\(b\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Regulations Group, Rotorcraft Directorate,
FAA. Operators shall submit their requests through an FAA Principal
Maintenance Inspector, who may concur or comment and then send it to the
Manager, Regulations Group.

Note 2: Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
Regulations Group.

\(c\) Special flight permits will not be issued allowing use of the
affected cargo hook.

\(d\) This amendment becomes effective on September 6, 2002.

Note 3: The subject of this AD is addressed in Direction Generale De
L\'Aviation Civile, (France) AD 2001-318(A), dated July 25, 2001.

**FOR FURTHER INFORMATION CONTACT:** Jim Grigg, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort
Worth, Texas 76193-0110, telephone (817) 222-5490, fax (817) 222-5961.

Issued in Fort Worth, Texas, on July 24, 2002.

Eric Bries,

Acting Manager, Rotorcraft Directorate, , Aircraft Certification
Service.

\[FR Doc. 02-19488 Filed 8-1-02; 8:45 am\]

BILLING CODE 4910-13-P