**FEDERAL AVIATION ADMINISTRATION**

**AIRWORTHINESS DIRECTIVES**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS,**

**BALLOONS, & AIRSHIPS**

**BIWEEKLY 2002-15**

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
                            Internatioanal    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 |         |                |                                 |
+--------+---------+----------------+---------------------------------+

**BW 2002-15**

**TELEDYNE CONTINENTAL MOTORS**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

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

**CORRECTION:** *\[Federal Register: July 26, 2002 (Volume 67, Number
144); Page 48753; www.access.gpo.gov/su_docs/aces/aces140.html\]*

**2002-13-04 Teledyne Continental Motors:** Amendment 39-12792. Docket
No. 2000-NE-19-AD. Supersedes AD 2000-11-51.

**Applicability**

This airworthiness directive (AD) is applicable to Teledyne Continental
Motors (TCM) C-125, C145, O-300, IO-360, TSIO-360, and LTSIO-520-AE
series reciprocating engines with Unison Industries (Slick) Magnetos,
models 6314, 6324, and 6364, with magneto serial numbers of 99110001
through 9912999 inclusive. These engines are used on, but not limited to
Cessna 170, 170A, 170B, 172, 172A through 172H, 172XP, 336, 337, and
T303, Beagle B242-C, Cirrus SR20 and SR22, Globe Swift GC-1A and GC-1B,
Maule M4, Piper PA-28R-201T and PA-34, and Reims (Cessna) FA172, F337,
and FR172.

**Note 1:** The magneto serial number (SN) can be found in logbooks or
other maintenance records. If the magneto was installed, or if the
engine was assembled new, rebuilt, or overhauled before October 31,
1999, it is likely that a suspect magneto is not installed on the
engine.

**Note 2:** This airworthiness directive (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 (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**

Compliance with this AD is required within 10 flight hours after the
effective date of this AD, unless already done.

To prevent engine failure and loss of control of the airplane due to
migration of the magneto impulse coupling stop pin out of the magneto
frame and into the gear train of the engine, do the following:

**Replacement of Magneto**

\(a\) Replace any magneto that has a SN of 99110001 through 99129999,
inclusive, with a magneto that does not have a serial number in that
range.

**Inspections**

\(b\) Inspect each removed magneto to verify that the impulse coupling
stop pin is present. If the pin is missing, do the following:

\(1\) For C-125, C145, O-300, IO-360, and TSIO-360 series engines, do
the following:

\(i\) Remove magnetos, alternator or generator, and starter adapter from
the accessory case.

\(ii\) Remove the accessory case from the crankcase and oil sump.

\(iii\) Visually inspect the entire engine gear train for damaged or
broken gears and gear teeth.

\(iv\) Inspect visible portions of the engine crankcase and accessory
case for damage due to the stop pin becoming lodged between the engine
gear train and the crankcase or accessory case.

\(v\) If the accessory case is damaged, repair or replace the accessory
case.

\(vi\) If the engine crankcase is damaged, disassemble the engine, and
repair or replace the crankcase.

\(vii\) Inspect the oil pump drive gear teeth and inner cam gear teeth
for damage. Replace any engine drive train component that has been
damaged.

\(viii\) Replace any damaged gear, and magnaflux the mating gears using
the applicable engine overhaul manual.

\(2\) For LTSIO-520-AE series engines, do the following:

\(i\) Remove the starter adapter, fuel pump, vacuum pumps, accessory
drive pads, and both magnetos.

\(ii\) Visually inspect the entire engine gear train for damaged or
broken gears and gear teeth.

\(iii\) If any damage has occurred, remove the engine from the airplane,
disassemble the engine, and inspect it for damage. If any damage is
found, repair as necessary.

\(iv\) Replace any damaged gear, and magnaflux the mating gears using
the applicable engine overhaul manual.

\(v\) Inspect the interior portions of the engine crankcase for damage
due to the stop pin becoming lodged between the gear train and the
crankcase. If the crankcase is damaged, repair or replace the crankcase.

\(c\) After the effective date of this AD, do not install any Unison
Industries magnetos, model 6314, 6324, or 6364 that have a SN of
99110001 through 99129999 inclusive, on any engine.

**Note 3:** A cross-reference for part numbers (P/N\'s) for Unison
magneto model 6314 (TCM P/N 653271), model 6324 (TCM P/N 653292), and
model 6364 (TCM P/N 649696) can be found in TCM Mandatory Service
Bulletin 00-6A, dated June 8, 2000.

**Alternative Methods of Compliance**

\(d\) 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, Chicago Aircraft Certification Office
(CHIACO). Operators must submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, CHIACO.

**Note 4:** Information concerning the existence of approved alternative
methods of compliance with this airworthiness directive, if any, may be
obtained from the CHIACO.

**Special Flight Permits**

\(e\) 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 aircraft to a location where the requirements of
this AD can be done.

**Effective Date**

\(f\) This amendment becomes effective July 12, 2002.

**FOR FURTHER INFORMATION CONTACT:** Michael Downs, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des
Plaines, IL 60018; telephone (847) 294-7870, fax (847) 294-7834.

Issued in Burlington, Massachusetts, on June 17, 2002.

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

\[FR Doc. 02-16174 Filed 6-26-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**ROCKWELL COLLINS, INC.**

**AIRWORTHINESS DIRECTIVE**

**APPLIANCE**

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

**2002-14-19 Rockwell Collins, Inc.:** Amendment 39-12819; Docket No.
2000-CE-14-AD.

\(a\) *What airplanes are affected by this AD?* This AD affects the
following Rockwell Collins air data computers (ADC) that are installed
in, but not limited to the airplanes that are listed below:

\(1\) Affected ADC\'s:

+-----------------------------+------------+---------------------------+
| **Unit**                    | **Collins  | **Applicable to serial    |
|                             | part no.   | no.**                     |
|                             | (CPN)**    |                           |
+-----------------------------+------------+---------------------------+
| ADC--85 (Incorporating      | 622-       | All units.                |
| Rockwell Collins Service    | -8051--002 |                           |
| Bulletin No. 58)            |            |                           |
|                             | 622-       |                           |
|                             | -8051--003 |                           |
+-----------------------------+------------+---------------------------+
| ADC--85A (Incorporating     | 822-       | All units.                |
| Rockwell Collins Service    | -0370--113 |                           |
| Bulletin No. 58)            |            |                           |
|                             | 822-       |                           |
|                             | -0370--123 |                           |
|                             |            |                           |
|                             | 822-       |                           |
|                             | -0370--139 |                           |
|                             |            |                           |
|                             | 822-       |                           |
|                             | -0370--404 |                           |
|                             |            |                           |
|                             | 822-       |                           |
|                             | -0370--408 |                           |
+-----------------------------+------------+---------------------------+
| ADC--850D (Incorporating    | 822-       | All up to and including   |
| Rockwell Collins Service    | -0389--133 | 3DGW (except for 1P6D,    |
| Bulletin No. 58) \...       |            | 22RC--22RF, and           |
|                             |            | 23WK--3DGP).              |
+-----------------------------+------------+---------------------------+
| ADC--850F                   | 822-       | All Units.                |
|                             | -1036--406 |                           |
|                             |            |                           |
|                             | 822-       |                           |
|                             | -1036--418 |                           |
+-----------------------------+------------+---------------------------+

\(2\) List of airplanes where the affected ADC could be installed. This
is not a comprehensive list and airplanes not on this list that have the
ADC installed through field approval or other methods are still affected
by this AD:

  --------------------------- -------------------------------------------
  **Unit**                    **Airplane model**

  ADC-85/ADC-85A              Astra AIA.

                              Chinese Y7 and Y8.

                              Czech LET-610.

                              DC-8.

                              Falcon 20F.

                              Piaggio P-180.

                              Raytheon B200, B300, C90A and 1900D.

  ADC-850D                    Lear 60.

  ADC-850F                    Falcon 20, 50, and 50EX.
  --------------------------- -------------------------------------------

\(b\) *Who must comply with this AD?* Anyone who wishes to operate any
airplane that uses one of the above referenced Rockwell Collins air data
computers must comply with this AD.

\(c\) *What problem does this AD address?* The actions specified by this
AD are intended to prevent an unwarranted display of the ADC flag when
switching static air sources. This could cause the flight crew to react
to this incorrect flight information and possibly result in an unsafe
operating condition.

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

+--------------------------+------------+------------------------------+
| **Actions**              | **Co       | **Procedures**               |
|                          | mpliance** |                              |
+--------------------------+------------+------------------------------+
| \(1\) Perform the        | Within the | In accordance with Rockwell  |
| following, unless        | next 12    | Collins Service Bulletin No. |
| already accomplished:    | calendar   | 62, Revision No. 2,          |
|                          | months     | ADC--85/85A/8                |
| \(i\) Remove any         | after      | 50C/850D/850E/850F--34--62), |
| affected ADC from the    | August 23, | Revision No. 2, dated March  |
| airplanes.               | 2002 (the  | 7, 2000, or Service Bulletin |
|                          | effective  | No. 62, dated October 25,    |
| \(ii\) As applicable,    | date of    | 1999, as applicable, the     |
| replace or reprogram     | this AD).  | applicable Collins Computer  |
| parts or circuit card    |            | Component Maintenance        |
| assemblies on central    |            | Manual, and Collins Avionics |
| processing unit (CPU)    |            | Standard Shop Practices      |
| circuit cards.           |            | Instruction Manual.          |
|                          |            |                              |
| \(iii\) Test the ADC.    |            |                              |
|                          |            |                              |
| \(iv\) Install the       |            |                              |
| modified ADC in the      |            |                              |
| airplanes.               |            |                              |
+--------------------------+------------+------------------------------+
| \(2\) Do not install on  | As of      | In accordance with Rockwell  |
| any airplane one of the  | August 23, | Collins Service Bulletin No. |
| affected ADCs unless the | 2002 (the  | 62, Revision No. 2,          |
| modification and test    | Service    | ADC--85/85A/                 |
| required by paragraphs   | date of    | 850C/850D/850E/850F--34--62, |
| (d)(1)(ii) and           | this AD).  | dated arch 7, 2000, or       |
| (d)(1)(iii) of this AD   |            | Service Bulletin No. 62,     |
| are accomplished         |            | dated October 25, 1999, as   |
|                          |            | applicable.                  |
+--------------------------+------------+------------------------------+

**Note 1:** Rockwell Collins Operator Bulletin 99-7, dated August 1999,
contains information about an operational placard to install until
accomplishment of the actions of this AD. While not necessary to address
the unsafe condition in this AD, FAA highly recommends that you
incorporate this placard.

\(e\) *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, Wichita Aircraft 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, Wichita ACO.

**Note 2:** 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 Roger A. Souter, FAA,
Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room
100, Wichita, Kansas 67209; telephone: (316) 946-4134; facsimile: (316)
946-4407, E-mail: <Roger.Souter@faa.gov>.

\(g\) *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
Rockwell Collins Service Bulletin No. 62, Revision No. 2,
ADC-85/85A/850C/850D/850E/850F-34-62, dated March 7, 2000, or Rockwell
Collins Service Bulletin No. 62, ADC-85/85A/850C/850F-34-62, dated
October 25, 1999. 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 Rockwell Collins, Business and Regional Systems, 400
Collins Road Northeast, Cedar Rapids, Iowa 52498. 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 August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Roger A. Souter, FAA, Wichita
Aircraft Certification Office (ACO), 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4134; facsimile: (316)
946-4407. E-mail address: <Roger.Souter@faa.gov>.

Issued in Kansas City, Missouri, on July 3, 2002.

Dorenda D. Baker,

Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17306 Filed 7-12-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**PILATUS AIRCRAFT LTD.**

**AIRWORTHINESS DIRECTIVE**

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

**CORRECTION:** *\[Federal Register: July 24, 2002 (Volume 67, Number
142); Page 48510; www.access.gpo.gov/su_docs/aces/aces140.html\]*

**2002-14-22--Pilatus Aircraft Ltd.:** Amendment 39-12822; Docket No.
2001-CE-44-AD.

\(a\) *What airplanes are affected by this AD?* This AD affects the
following airplane models and serial numbers that are certificated in
any category:

\(1\) Group 1: Pilatus may have installed the affected bolts on the
following airplanes at manufacture. All portions of this AD apply to
these airplanes:

  ------------- ---------------------------------------------------------
  **Model**     **Serial Nos.**

  PC-12 and     349, 352, 357, 359, 362 through 365, 367, 369, 371, 375,
  PC-12/45      377, 380, 384, 385, 388, 390, 391, 393, 401, and 409.
  ------------- ---------------------------------------------------------

\(2\) Group 2: The affected bolts could be installed through spare
replacement on any of the following model airplanes. Paragraphs (d)(3)
and (d)(4) of this AD apply to these airplanes:

  ------------------------- ---------------------------------------------
  **Model**                 **Serial Nos.**

  PC-12 and PC-12/45        All serial numbers
  ------------------------- ---------------------------------------------

\(b\) *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 detect and replace defective main landing gear (MLG)
assembly bolts that have an improper cadmium plating, which could cause
hydrogen embrittlement and bolt failure.

\(d\) *What actions must I accomplish to address this problem?* To
address this problem, accomplish all actions for Group 1 airplanes, and
accomplish paragraphs (d)(3) and (d)(4) of this AD for Group 2
airplanes:

+----------------------------------+----------------+-----------------+
| **Actions**                      | **Compliance** | **Procedures**  |
+----------------------------------+----------------+-----------------+
| \(1\) Inspect the left and right | Inspect within | Pilatus PC--12  |
| main landing gear (MLG) assembly | the next 30    | Service         |
| for the existence of a bolt,     | days after     | bulletin No.    |
| part number (P/N) 532.10.12.077, | August 29,     | 32--012, dated  |
| that has a serial number (S/N)   | 2002 (the      | October 18,     |
| with both the letters ''AT'' and | effective date | 2001, provides  |
| a number of 299 or lower.        | of this AD).   | information     |
|                                  | Prior to       | about these     |
| \(i\) If the above referenced    | further        | actions.        |
| bolts are not installed, no      | flight,        |                 |
| further action is required.      | replace bolts  |                 |
|                                  | found during   |                 |
| \(ii\) If the above referenced   | the inspection |                 |
| bolts are installed, replace     | required in    |                 |
| each bolt with an FAA-approved   | paragraph      |                 |
| bolt that does not have a S/N    | (d)(1) of this |                 |
| with both the letters ''AT'' and | AD.            |                 |
| a number of 299 or lower.        |                |                 |
+----------------------------------+----------------+-----------------+
| \(2\) Send the removed bolts to  | Within 10 days | Send the        |
| Pilatus Aircraft Ltd. so the     | after removing | removed bolts   |
| bolts cannot be reused and       | the bolts or   | to Pilatus      |
| report the results of the        | within 10 days | Aircraft Ltd.   |
| inspection (positive or          | after August   | at the address  |
| negative) to FAA. The Office of  | 29, 2002 (the  | in paragraph    |
| Management and Budget (OMB)      | effective date | (h) of this AD, |
| approved the information         | of this AD),   | and send the    |
| collection requirements          | whichever      | report to Doug  |
| contained in this regulation     | occurs later.  | Rudolph, FAA,   |
| under the provisions of the      |                | at the address  |
| Paperwork Reduction Act of 1980  |                | in paragraph    |
| (44 U.S.C. 3501 *et seq.*) and   |                | (f) of this AD. |
| assigned OMB Control Number      |                |                 |
| 2120--0056.                      |                |                 |
+----------------------------------+----------------+-----------------+
| \(3\) Do not install any bolt,   | As of August   | Not Applicable. |
| P/N 532.10.12.077, on any MLG    | 29, 2002 (the  |                 |
| assembly that has a S/N with     | effective date |                 |
| both the letters ''AT'' and a    | of this AD).   |                 |
| number of 299 or lower.          |                |                 |
+----------------------------------+----------------+-----------------+
| \(4\) If you have already        | Within the     | Not Applicable. |
| accomplished the actions         | next 30 days   |                 |
| specified in Pilatus PC--12      | after August   |                 |
| Service Bulletin No. 32--012,    | 29, 2002 (the  |                 |
| dated October 18, 2001, send a   | effective date |                 |
| report to the FAA at the address | of this AD).   |                 |
| in paragraph (f) of this AD,     |                |                 |
| stating if one of the affected   |                |                 |
| bolts was replaced and returned  |                |                 |
| to Pilatus.                      |                |                 |
+----------------------------------+----------------+-----------------+

\(e\) *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, Small Airplane Directorate, approves your
alternative. Submit your request through an FAA Principal Maintenance
Inspector, who may add comments and then send it to the Manager, Small
Airplane Directorate.

**Note 1:** 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 Doug Rudolph, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4059; facsimile: (816)
329-4090.

\(g\) *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
Pilatus PC-12 Service Bulletin No. 32-012, dated October 18, 2001. 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 Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224; or
from Pilatus Business Aircraft Ltd., Product Support Department, 11755
Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-9099;
facsimile: (303) 465-6040. 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 August 29, 2002.

**FOR FURTHER INFORMATION CONTACT:** Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

Issued in Kansas City, Missouri, on July 8, 2002.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02-17602 Filed 7-15-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**TURBOMECA S.A.:**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

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

**2002-14-26 Turbomeca S.A.:** Amendment 39-12826. Docket No.
2001-NE-35-AD.

**Applicability:** This airworthiness directive (AD) is applicable to
Turbomeca S.A. Arriel models 1A, 1A1, 1B, 1D, and 1D1 turboshaft
engines. These engines are installed on, but not limited to, Astar
AS350D; Eurocopter AS350B, BA, B1, L1, and B2N; and Fennic AS550U2
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 as indicated, unless
already done.

To prevent uncontainment of the free turbine during an overspeed event,
resulting in damage to the helicopter, do the following:

\(a\) For Arriel engine models 1A and 1A1 that have incorporated
modification TU 13, but have not incorporated modification TU 99 and
modification TU 215, and for Arriel engine models 1B and 1D that have
not incorporated modification TU 99 and modification TU 215, do the
following within 30 days after the effective date of this AD:

\(1\) Install containment shield ring in accordance with the
Instructions to be Incorporated, paragraphs 2A. through 2C,
(modification TU 254) of service bulletin (SB) No. A292 72 0206, Update
2, dated October 23, 2000.

\(2\) Install double support around the reduction gearbox free turbine
bearing housing, in accordance with Instructions for Incorporation,
paragraphs 2A. through 2C, (modification TU 259) of SB No. 292 72 0208,
Update 2, dated May 13, 1996.

\(b\) For Arriel engine models 1A and 1A1 that have incorporated
modification TU 13 and modification TU 99, but have not incorporated
modification TU 215, and Arriel engine models 1B, 1D, and 1D1 that have
incorporated modification TU 99, but have not incorporated modification
TU 215, do the following within 30 days after the effective date of this
AD:

\(1\) Install additional containment shield ring, in accordance with the
Instructions to be Incorporated, paragraphs 2A. through 2C,
(modification TU 255) of SB No. A292 72 0207, Update 2, dated October
23, 2000.

\(2\) Install double support around the reduction gearbox free turbine
bearing housing, in accordance with Instructions for Incorporation,
paragraphs 2A. through 2C, (modification TU 259) of SB No. 292 72 0208,
Update 2, dated May 13, 1996.

**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 requests 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 modifications must be done in accordance with the following
Turbomeca S.A. mandatory service bulletins (MSB\'s):

  ------------------------------ ------------ -------------- --------------
  **Document No.**               **Pages**    **Revision**   **Date**

  MSB No. A292 72 0206, Total    All          2              Oct. 23, 2000.
  pages: 8                                                   

  MSB No. A292 72 0207, Total    All          2              Oct. 23, 2000.
  pages: 7                                                   

  MSB No. 292 72 0208, Total     All          2              May 13, 1996.
  pages: 8                                                   
  ------------------------------ ------------ -------------- --------------

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 S.A., 40220 Tarnos, France;
telephone: (33) 05 59 64 40 00; fax: (33) 05 59 64 60 80. 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.

**Note 3:** The subject of this AD is addressed in Direction Generale de
L\'Aviation Civile airworthiness directive AD 1995-069(A)R3.

**Effective Date**

\(f\) This amendment becomes effective on August 6, 2002.

**FOR FURTHER INFORMATION CONTACT:** Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park; Burlington, MA 01803-5299,
telephone (781) 238-7175; fax (781) 238-7199.

Issued in Burlington, Massachusetts, on July 8, 2002.

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

\[FR Doc. 02-18203 Filed 7-19-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**DE HAVILLAND INC.:**

**AIRWORTHINESS DIRECTIVE**

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

**2002-14-28 de Havilland Inc.:** Amendment 39-12828; Docket No.
98-CE-124-AD.

\(a\) *What airplanes are affected by this AD?* This AD affects all
serial numbers of Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III
airplanes 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 structural failure of the front fuselage
caused by corrosion or fatigue damage to the struts that develops over
time, which could result in reduced or loss of control of the airplane.

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

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

  \(1\) Replace each front Initially replace upon  In accordance with the
  fuselage strut with a    accumulating 15 years   applicable maintenance
  new strut. Part numbers  on each front fuselage  manual, as specified
  for existing and         strut or within the     in de Havilland Parts
  replacement front        next 12 calendar months Service Manual
  fuselage struts parts    after September 6, 2002 1--2--2, Part 5,
  are presented in         (the effective date of  Temporary Revision
  paragraph (e) of this    this AD), whichever     2--22; and de
  AD.                      occurs later.           Havilland Parts
                           Repetitively replace    Service Manual
                           thereafter upon         1--2T--2, Part 5,
                           accumulating 15 years   Temporary Revision
                           on each front fuselage  2T--6, both dated
                           strut.                  August 3, 1998.
  ------------------------ ----------------------- ----------------------

+-----------------------+----------------------+----------------------+
| \(2\) As an           | Initially inspect    | For the detailed     |
| alternative method of | upon accumulating 15 | inspection, use an   |
| compliance to the     | years on each front  | inspection light,    |
| replacements in       | fuselage strut or    | inspection mirror,   |
| paragraph (d)(1) of   | within the next 12   | and 10X magnifying   |
| this AD, you may      | calendar months      | glass. For the       |
| repetitively inspect  | after September 6,   | ultrasonic           |
| each front fuselage   | 2002 (the effective  | inspection, use      |
| strut, as follows:.   | date of this AD),    | FAA-approved         |
|                       | whichever occurs     | procedures that      |
| \(i\) perform a       | later. Accomplish    | follow a similar     |
| detailed inspection   | the repetitive       | calibration and      |
| of each front         | detailed inspection  | measures strut       |
| fuselage strut and    | thereafter at        | thickness to that    |
| all fittings attached | intervals not to     | detailed in          |
| to the frame for      | exceed 12 months and | Bombardier Service   |
| damage (corrosion,    | the ultrasonic       | Bulletin 2/49,       |
| cracks, dents). When  | thickness            | Revision C.          |
| fatigue damage is     | measurement at       |                      |
| found, you must       | intervals not to     |                      |
| replace the damaged   | exceed 5 years.      |                      |
| strut. After each     | Accomplish the       |                      |
| inspection, clean the | corrosion prevention |                      |
| drain holes around    | work prior to        |                      |
| the bottom end        | further flight after |                      |
| fitting and protect   | each inspection.     |                      |
| the tube with an      | Accomplish the       |                      |
| appropriate corrosion | replacement prior to |                      |
| preventive spray.     | further flight after |                      |
| Part numbers for      | damage is found or   |                      |
| existing and          | the thickness is     |                      |
| replacement front     | found below 0.030    |                      |
| fuselage struts parts | inches. Then, after  |                      |
| are presented in      | replacement either   |                      |
| paragraph (e) of this | replace with a new   |                      |
| AD.                   | strut at 15year      |                      |
|                       | intervals thereafter |                      |
| \(ii\) perform an     | or repetitively      |                      |
| ultrasonic thickness  | inspect as           |                      |
| measurement of all    | prescribed above     |                      |
| surface on each front | beginning at 15      |                      |
| fuselage strut. When  | years after each     |                      |
| minimum thickness is  | replacement.         |                      |
| below 0.030 inches,   |                      |                      |
| you must replace the  |                      |                      |
| affected strut. Part  |                      |                      |
| numbers for existing  |                      |                      |
| and replacement front |                      |                      |
| fuselage struts parts |                      |                      |
| are presented in      |                      |                      |
| paragraph (e) of this |                      |                      |
| AD.                   |                      |                      |
+-----------------------+----------------------+----------------------+
| \(3\) Do not install, | As of September 6,   | Not Applicable.      |
| on any affected       | 2002 (the effective  |                      |
| airplane, any front   | date of this AD.     |                      |
| fuselage strut unless |                      |                      |
| it has a part number  |                      |                      |
| specified in the      |                      |                      |
| Replacement Part      |                      |                      |
| Number column of the  |                      |                      |
| chart presented in    |                      |                      |
| paragraph (e) of this |                      |                      |
| AD.                   |                      |                      |
+-----------------------+----------------------+----------------------+

\(e\) *What part number front fuselage struts should I use for
replacements?* The following charts presents the part numbers for
existing parts and replacement parts for the front fuselage strut
replacements:

  ---------------------- ------------------ ------------------------------
  **Installed part No.** **Replacement part **Description**
                         No.**              

  C2FS209 or C2FS3281A   C2FS3281A          Strut Assembly Front Fuselage,
                                            Left.

  C2FS210 or C2FS3282A   C2FS3282A          Strut Assembly Front Fuselage,
                                            Right.
  ---------------------- ------------------ ------------------------------

\(f\) *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, New York Aircraft 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, New York ACO.

**Note 1:** 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 (f) 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.

\(g\) *Where can I get information about any already-approved
alternative methods of compliance?* Contact Jon Hjelm, Aerospace
Engineer, FAA, New York Aircraft Certification Office, 10 Fifth Street,
Third Floor, Valley Stream, New York 11581; telephone: (516) 256-7523;
facsimile: (516) 256-2716.

\(h\) *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.

\(i\) *How do I get copies of the documents referenced in this AD?* You
may direct technical questions to or get copies of the documents
referenced in this AD from Bombardier Inc., Bombardier Regional Aircraft
Division, 123 Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5;
telephone: (416) 633-7310. You may view these documents at FAA, Central
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas
City, Missouri 64106.

**Note 2:** The subject of this AD is addressed in Canadian AD
CF-98-37R1, dated August 20, 1999.

\(j\) *When does this amendment become effective?* This amendment
becomes effective on September 6, 2002.

**FOR FURTHER INFORMATION CONTACT:** Mr. Jon Hjelm, Aerospace Engineer,
New York Aircraft Certification Office, 10 Fifth Street, 3rd Floor,
Valley Stream, New York 11581-1200; telephone: (516) 256-7523;
facsimile: (516) 568-2716.

Issued in Kansas City, Missouri, on July 15, 2002.

Dorenda D. Baker,

Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-18334 Filed 7-19-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**DIAMOND AIRCRAFT INDUSTRIES GMBH**

**AIRWORTHINESS DIRECTIVE**

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

**2002-15-01 Diamond Aircraft Industries GMBH:** Amendment 39-12829;
Docket No. 2002-CE-11-AD.

\(a\) *What sailplanes are affected by this AD?* This AD affects Models
H-36 \'\'Dimona\'\', 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 sailplanes, all serial numbers, that are certificated in any
category.

\(b\) *Who must comply with this AD?* Anyone who wishes to operate any
of the sailplanes 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 detect and correct damage in the long aileron push
control rods, which could result in failure of the aileron push rods and
decreased control. Such failure could lead to aeroelastic flutter.

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

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

  \(1\) Inspect the  Within the next   In accordance with paragraph 1.8
  long aileron push  10 hours          Measures of Diamond Aircraft
  rods in both       time-in-service   Industries GmbH Service Bulletin No.
  wings.             (TIS) after       MSB36--72, dated February 1, 2002;
                     September 3, 2002 Diamond Aircraft Industries GmbH Work
                     (the effective    Instruction No. WI--MSB36--72, dated
                     date of this AD). February 1, 2002; and the applicable
                                       sailplane maintenance manual.

  \(2\) If any long  Before further    In accordance with paragraph 1.8
  aileron push rods  flight, after the Measures of Diamond Aircraft
  are found damaged  inspection        Industries GmbH Service Bulletin No.
  during the         required in       MSB36--72, dated February 1, 2002;
  inspection         paragraph (d)(1)  Diamond Aircraft Industries GmbH Work
  required in        of this AD.       Instruction No. WI--MSB36--72, dated
  paragraph (d)(1)                     February 1, 2002; and the applicable
  of this AD, modify                   sailplane maintenance manual.
  the push rods.                       

  \(3\) If no damage Within the next   In accordance with paragraph 1.8
  is found during    25 hours TIS      Measures of Diamond Aircraft
  the inspection     after September   Industries GmbH Service Bulletin No.
  required in        3, 2002 (the      MSB36--72, dated February 1, 2002;
  paragraph (d)(1),  effective date of Diamond Aircraft Industries GmbH Work
  modify the push    this AD).         Instruction No. WI--MSB36--72, dated
  rods.                                February 1, 2002; and the applicable
                                       sailplane maintenance manual.
  ------------------ ----------------- -------------------------------------

\(e\) *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 Standards Office Manager, Small Airplane Directorate, approves
your alternative. Submit your request through an FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Standards Office Manager.

**Note 1:** This AD applies to each sailplane 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
sailplanes 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 Mike Kiesov, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4144; facsimile: (816)
329-4090.

\(g\) *What if I need to fly the sailplane 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 sailplane 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
Diamond Aircraft Industries GmbH Service Bulletin No. MSB36-72, dated
February 1, 2002; and Diamond Aircraft Industries GmbH Work Instruction
No. WI-MSB36-72, dated February 1, 2002. 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 Diamond Aircraft Industries
GmbH, N.A. Otto-Strasse 5, A-2700 Wiener Neistadt, Austria; telephone:
43 2622 26 700; facsimile: 43 2622 26 780. 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.

Note 2: The subject of this AD is addressed in Austrian AD No. 111,
dated February 26, 2002.

\(i\) *When does this amendment become effective?* This amendment
becomes effective on September 3, 2002.

**FOR FURTHER INFORMATION CONTACT:** Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4144; facsimile: (816) 329-4090.

Issued in Kansas City, Missouri, on July 12, 2002.

Dorenda D. Baker,

Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-18333 Filed 7-19-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**HAMILTON SUNDSTRAND POWER SYSTEMS**

**AIRWORTHINESS DIRECTIVE**

**APPLIANCE**

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

**2002-15-02 Hamilton Sundstrand Power Systems (formerly Sundstrand
Power Systems, Turbomach, and Solar):** Amendment 39-12830. Docket No.
2002-NE-01-AD.

**Applicability**

This airworthiness directive (AD) is applicable to Hamilton Sundstrand
Power Systems (formerly Sundstrand Power Systems, Turbomach, and Solar)
models T-62T-2C, T-62T-25, T-62T-29, and T-62T-39 auxiliary power units
(APU\'s) that have compressor wheel part number (P/N) 100636-1
installed. These APU\'s are installed on, but not limited to, Fairchild
FH-227, Dassault Falcon 20, Lockheed 1329 series (Jetstar), British
Aerospace Jetstream 3101, Raytheon Aircraft HS125-600, -700, -800, and
Sabreliner Corporation 60 and 80 airplanes, and Boeing Defense & Space
Group 234 Series helicopters.

**Note 1:** This AD applies to each APU 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 APU\'s 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**

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

To replace affected compressor wheels

P/N 100636-1, which if not replaced, could result in uncontained
compressor wheel failure and damage to the airplane, do the following:

**Cast Steel Compressor Wheel Replacement**

\(a\) For compressor wheels, P/N 100636-1, made of cast steel,
identifiable by a four-digit casting lot vendor identification number
used as a prefix to the serial number, replace compressor wheels with
compressor wheel P/N 4503164, 4504174, or M4504174 as follows:

\(1\) Replace cast steel compressor wheels with 2,350 or greater
cycles-since-new (CSN) on the effective date of this AD within 250
cycles-in-service (CIS) after the effective date of this AD.

\(2\) Replace cast steel compressor wheels with less than 2,350 CSN on
the effective date of this AD before accumulating 2,600 CSN.

**Wrought Steel Compressor Wheel Replacement**

\(b\) For compressor wheels, P/N 100636-1 made of wrought steel,
identifiable by a serial number beginning with the letter W, replace
compressor wheels with compressor wheel P/N 4503164, 4504174, or
M4504174 as follows:

\(1\) Replace wrought steel compressor wheels with 3,600 or greater CSN
on the effective date of this AD within 500 CIS after the effective date
of this AD.

\(2\) Replace wrought steel compressor wheels with less than 3,600 CSN
on the effective date of this AD before accumulating 4,100 CSN.

\(c\) Information on procedures for replacing compressor wheel P/N
100636-1 may be found in Hamilton Sundstrand Power Systems service
bulletin No. SB-T-62T-49-148, Revision 1, dated December 20, 2001.

**Reduced Life Limits**

\(d\) This AD establishes new cyclic life limits for compressor wheels
P/N 100636-1, of 2,600 CSN for cast steel compressor wheels and 4,100
CSN for wrought steel compressor wheels. Except as provided in paragraph
(e) of this AD, no alternate life limits for these parts may be
approved.

**Alternative Methods of Compliance**

\(e\) 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
(ACO). Operators must submit their request 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 airworthiness directive, if any, may be
obtained from the Los Angeles ACO.

**Special Flight Permits**

\(f\) 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 aircraft to a location where the requirements of
this AD can be done.

**Effective Date**

\(g\) This amendment becomes effective on August 28, 2002.

**FOR FURTHER INFORMATION CONTACT:** Roger Pesuit, Aerospace Engineer,
Los Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone
(562) 627-5251, fax (562) 627-5210.

Issued in Burlington, Massachusetts, on July 15, 2002.

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

\[FR Doc. 02-18482 Filed 7-23-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**SIKORSKY AIRCRAFT CORPORATION**

**AIRWORTHINESS DIRECTIVE**

**EMERGENCY**

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

**2002-15-51 SIKORSKY AIRCRAFT CORPORATION: Docket No. 2002-SW-40-AD.**

Applicability: Model S-76A, B, and C helicopters, 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: Required before further flight, unless accomplished
previously.

To prevent failure of a main rotor blade (blade) and subsequent loss of
control of the helicopter, accomplish the following:

\(a\) Review the blade service records and other records in accordance
with the Accomplishment Instructions, paragraphs 3.A.(1), (2), and (3),
of Sikorsky Aircraft Corporation Alert Service Bulletin No. 76‑65-55A,
dated July 25, 2002, for evidence of damage to a blade due to a
lightning strike. Before further flight, remove any blade identified as
having been damaged by lightning.

\(b\) Remove blades, serial number A086-00167, 00429, 00798, 00999,
01165, 01168, 01291, and 02504, which are known to have sustained
lightning damage.

\(c\) If the blade service history cannot be determined, remove the
blade from service before further flight.

\(d\) After the effective date of this AD, should a blade be subjected
to lightning strike damage, remove the blade from service before the
next flight.

\(e\) 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, Boston Aircraft 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, Boston Aircraft Certification Office. Blades removed from
service in accordance with this AD may be returned to service under a
process approved by the Manager, Boston Aircraft Certification Office.

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

\(f\) Special flight permits will not be issued.

\(g\) Copies of the applicable service information may be obtained from
Sikorsky Aircraft Corporation, Attn: Manager, Commercial Tech Support,
6900 Main Street, Stratford, Connecticut 06614, phone (203) 386-3001,
fax (203) 386-5983.

\(h\) **Emergency AD 2002-15-51, issued July 26, 2002, becomes effective
upon receipt.**

FOR FURTHER INFORMATION CONTACT: Richard Noll, Aviation Safety Engineer,
Boston Aircraft Certification Office, 12 New England Executive Park,
Burlington, MA 01803, telephone (781) 238-7160, fax (781) 238-7170.

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

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.