**FEDERAL AVIATION ADMINISTRATION**

**AIRWORTHINESS DIRECTIVES**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS,**

**BALLOONS, & AIRSHIPS**

**BIWEEKLY 2002-12**

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

  2002-12-02                Eurocopter France Rotorcraft: AS332L2

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

**BW 2002-12**

**AIR TRACTOR, INC.**

**AIRWORTHINESS DIRECTIVE**

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

**CORRECTION:** *Minor typographical errors exist in the Federal
Register printing of this document and on the Government Printing Office
(GPO) website. The FAA has requested a correction be made to both the
Federal Register and GPO website. This copy reflects the corrections.*

**2002--11--03 Air Tractor, Inc.:** Amendment 39--12764; Docket No.
2002--CE--10--AD.

\(a\) *What airplanes are affected by this AD?* This AD applies to
certain Models AT--502, AT--502A, AT--502B, and AT-503A airplanes. Use
paragraph (a)(1) of this AD for airplanes that do not incorporate and
never have incorporated winglets. Use paragraph (a)(3) of this AD for
certain AT--500 series airplanes that incorporate or have incorporated
Marburger Enterprises, Inc. winglets.

\(1\) The following presents airplanes (certificated in any category)
that are affected by this AD, along with the new safe life (presented in
hours time-in-service (TIS)) of the wing lower spar cap for all affected
airplane models and serial numbers:

+----------------+----------------------------------+------------------+
| > **Model**    | > **Serial Nos.**                | > **Safe life**  |
+----------------+----------------------------------+------------------+
| > AT--502      | > 0003 through 0236              | > 2,050 hours    |
|                |                                  | > TIS.           |
+----------------+----------------------------------+------------------+
| > AT--502A     | > 0158 through 0618              | > 1,650 hours    |
|                |                                  | > TIS.           |
+----------------+----------------------------------+------------------+
| > AT--502B     | > 0187 through 0618              | > 2,050 hours    |
|                |                                  | > TIS.           |
+----------------+----------------------------------+------------------+
| > AT--503A     | > All serial numbers beginning   | > 2,050 hours    |
|                | > with 0067                      | > TIS            |
+----------------+----------------------------------+------------------+

\(2\) If piston powered aircraft have been converted to turbine power,
you must use the limits for the corresponding serial number
turbine-powered aircraft.

\(3\) The following presents airplanes (certificated in any category)
that could incorporate or could have incorporated Marburger Enterprises,
Inc. winglets. These winglets are installed in accordance with
Supplemental Type Certificate (STC) SA00490LA. Use the winglet usage
factor in the table below, the safe life specified in paragraph (a)(1)
of this AD, and the instructions included in the Appendix to this AD to
determine the new safe life of these airplanes:

+--------------+----------------------------+--------------------------+
| > **Model**  | > **Serial Nos.**          | > **Winglet usage        |
|              |                            | > Factor**               |
+--------------+----------------------------+--------------------------+
| > AT--502    | > 0003 through 0236        | > 1.6                    |
+--------------+----------------------------+--------------------------+
| > AT--502A   | > 0158 through 0238        | > 1.6                    |
+--------------+----------------------------+--------------------------+
| > AT--502A   | > 0239 through 0618        | > 1.2                    |
+--------------+----------------------------+--------------------------+
| > AT--502B   | > 0187 through 0618        | > 1.2                    |
+--------------+----------------------------+--------------------------+

\(b\) *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 fatigue cracks from occurring in the wing
lower spar cap before the established safe life is reached. Fatigue
cracks in the wing lower spar cap, if not detected and corrected, could
result in the wing separating from the airplane during flight.

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

+--------------------------+-------------------+----------------------+
| > **Actions**            | > **Compliance**  | > **Procedures**     |
+--------------------------+-------------------+----------------------+
| > \(1\) Modify the       | > Accomplish the  | > The owner/operator |
| > applicable aircraft    | > logbook entry   | > holding at least a |
| > records (logbook) as   | > within the next | > private pilot      |
| > follows to show the    | > 10 hours TIS    | > certificate as     |
| > reduced safe life for  | > after June 14,  | > authorized by      |
| > the wing lower spar    | > 2002 (the       | > section 43.7 of    |
| > cap (use the           | > effective date  | > the Federal        |
| > information from the   | > of this AD).    | > Aviation           |
| > table in paragraph     |                   | > Regulations (14    |
| > (a)(1) of this AD and  |                   | > CFR 43.7) may      |
| > utilize the            |                   | > modify the         |
| > information in         |                   | > aircraft records   |
| > paragraph (a)(3) of    |                   | > as specified in    |
| > this AD and the        |                   | > paragraphs         |
| > Appendix to this AD,   |                   | > (d)(1)(i) and      |
| > as applicable):        |                   | > (d)(1)(ii) of this |
|                          |                   | > AD. Make an entry  |
|                          |                   | > into the aircraft  |
|                          |                   | > records showing    |
|                          |                   | > compliance with    |
|                          |                   | > this portion of AD |
|                          |                   | > in accordance with |
|                          |                   | > section 43.9 of    |
|                          |                   | > the Federal        |
|                          |                   | > Aviation           |
|                          |                   | > Regulations (14    |
|                          |                   | > CFR 43.9).         |
|                          |                   | > Accomplish the     |
|                          |                   | > actual             |
|                          |                   | > repl               |
|                          |                   | acement/modification |
|                          |                   | > in accordance with |
|                          |                   | > Snow Engineering   |
|                          |                   | > Service Letter     |
|                          |                   | > #197 or #205, both |
|                          |                   | > Revised March 26,  |
|                          |                   | > 2001, as           |
|                          |                   | > applicable. The    |
|                          |                   | > owner/ operator    |
|                          |                   | > may not accomplish |
|                          |                   | > the                |
|                          |                   | > repla              |
|                          |                   | cement/modification, |
|                          |                   | > unless he/she      |
|                          |                   | > holds the proper   |
|                          |                   | > mechanic           |
|                          |                   | > authorization.     |
+--------------------------+-------------------+----------------------+
| > \(i\) Incorporate the  |                   |                      |
| > following into the     |                   |                      |
| > Aircraft Logbook ''In  |                   |                      |
| > accordance with AD     |                   |                      |
| > 2002--11--03, the wing |                   |                      |
| > lower spar cap is life |                   |                      |
| > limited to \_\_\_\_.'' |                   |                      |
| > Insert the applicable  |                   |                      |
| > safe life number from  |                   |                      |
| > the applicable tables  |                   |                      |
| > in paragraphs (a)(1)   |                   |                      |
| > and (a)(3) of this AD  |                   |                      |
| > and the Appendix to    |                   |                      |
| > this AD)               |                   |                      |
+--------------------------+-------------------+----------------------+
| > \(ii\) If, as of the   |                   |                      |
| > time of the logbook    |                   |                      |
| > entry requirement of   |                   |                      |
| > paragraph (d)(1)(i) of |                   |                      |
| > this AD, your airplane |                   |                      |
| > is over or within 50   |                   |                      |
| > hours of the safe      |                   |                      |
| > life, an additional 50 |                   |                      |
| > hours TIS is allowed   |                   |                      |
| > to accomplish the      |                   |                      |
| > replacement/           |                   |                      |
| > modification.          |                   |                      |
+--------------------------+-------------------+----------------------+
| > \(2\) If you have      | > Inspect prior   | > In accordance with |
| > ordered parts from the | > to further      | > the procedures in  |
| > factory when it is     | > flight after    | > Snow Engineering   |
| > time to replace the    | > ordering the    | > Service Letter     |
| > wing lower spar cap    | > parts and       | > #197 or #205, both |
| > (as required when you  | > thereafter at   | > Revised March 26,  |
| > reach the established  | > intervals not   | > 2001, as           |
| > safe life), but the    | > to exceed 400   | > applicable.        |
| > parts are not          | > hours TIS until |                      |
| > available, you may     | > one of the      |                      |
| > eddy-current inspect   | > criteria in     |                      |
| > the wing lower spar    | > paragraphs      |                      |
| > cap. These inspections | > (d)(2)(i),      |                      |
| > are allowed until one  | > (d)(2)(ii), and |                      |
| > of the following       | > (d)(2)(iii) of  |                      |
| > occurs, at which time  | > this AD is met. |                      |
| > the                    |                   |                      |
| >                        |                   |                      |
| replacement/modification |                   |                      |
| > must be accomplished:  |                   |                      |
+--------------------------+-------------------+----------------------+
| > \(i\) Crack(s) is/are  |                   |                      |
| > found;                 |                   |                      |
+--------------------------+-------------------+----------------------+
| > \(ii\) Parts become    |                   |                      |
| > available from the     |                   |                      |
| > manufacturer; or       |                   |                      |
+--------------------------+-------------------+----------------------+

+--------------------------+--------------------+---------------------+
| > \(iii\) Not more than  |                    |                     |
| > three inspections or   |                    |                     |
| > 1,200 hours TIS go by: |                    |                     |
| > the first inspection   |                    |                     |
| > would have to be       |                    |                     |
| > accomplished upon      |                    |                     |
| > accumulating the safe  |                    |                     |
| > life; the second       |                    |                     |
| > inspection would have  |                    |                     |
| > to be accomplished     |                    |                     |
| > within 400 hours TIS   |                    |                     |
| > after accumulating the |                    |                     |
| > safe life; the third   |                    |                     |
| > inspection would have  |                    |                     |
| > to be accomplished 400 |                    |                     |
| > hours TIS after the    |                    |                     |
| > second inspection; and |                    |                     |
| > the                    |                    |                     |
| >                        |                    |                     |
| replacement/modification |                    |                     |
| > would have to be       |                    |                     |
| > accomplished within    |                    |                     |
| > 400 hours TIS after    |                    |                     |
| > the third inspection   |                    |                     |
| > (maximum elapsed time  |                    |                     |
| > would be 1,200 hours   |                    |                     |
| > TIS).                  |                    |                     |
+--------------------------+--------------------+---------------------+
| > \(3\) Eddy-current     | > Immediately      | > In accordance     |
| > inspect the wing lower | > prior to the     | > with the          |
| > spar cap in order to   | > replac           | > procedures in     |
| > detect any crack       | ement/modification | > Snow Engineering  |
| > before it extends to   | > required when    | > Service Letter    |
| > the modified center    | > you reach the    | > #197 or #205,     |
| > section of the wing    | > new safe life.   | > both Revised      |
| > and repair that crack  | > For airplanes    | > March 26, 2001,   |
| > or replace the wing    | > that had this    | > as applicable.    |
| > section. The           | > replac           |                     |
| > inspection must be     | ement/modification |                     |
| > accomplished by one of | > accomplished in  |                     |
| > the following:         | > accordance with  |                     |
|                          | > either AD        |                     |
|                          | > 2001--10--04 or  |                     |
|                          | > AD 2001--10-- 04 |                     |
|                          | > R1, accomplish   |                     |
|                          | > this inspection  |                     |
|                          | > and any          |                     |
|                          | > necessary        |                     |
|                          | > corrective       |                     |
|                          | > action within    |                     |
|                          | > the next 400     |                     |
|                          | > hours TIS after  |                     |
|                          | > June 14, 2002    |                     |
|                          | > (the effective   |                     |
|                          | > date of this     |                     |
|                          | > AD), unless      |                     |
|                          | > already          |                     |
|                          | > accomplished     |                     |
|                          | > (have the        |                     |
|                          | > mechanic who     |                     |
|                          | > accomplished the |                     |
|                          | > work mark the    |                     |
|                          | > logbooks         |                     |
|                          | > accordingly).    |                     |
+--------------------------+--------------------+---------------------+
| > \(i\) a Level 2 or     |                    |                     |
| > Level 3 inspector that |                    |                     |
| > is certified for       |                    |                     |
| > eddy-current           |                    |                     |
| > inspection using the   |                    |                     |
| > guidelines established |                    |                     |
| > by the American        |                    |                     |
| > Society for            |                    |                     |
| > Nondestructive Testing |                    |                     |
| > or MIL--STD--410; or   |                    |                     |
+--------------------------+--------------------+---------------------+
| > \(ii\) A person        |                    |                     |
| > authorized to perform  |                    |                     |
| > AD work who has        |                    |                     |
| > completed and passed   |                    |                     |
| > the Air Tractor, Inc.  |                    |                     |
| > training course on     |                    |                     |
| > Eddy Current           |                    |                     |
| > Inspection on wing     |                    |                     |
| > lower spar caps.       |                    |                     |
+--------------------------+--------------------+---------------------+
| > \(4\) Report to FAA    | > Within 10 days   | > Submit the form   |
| > the results of each    | > after the        | > (Figure 1 of this |
| > inspection required by | > inspection       | > AD) to FAA, Fort  |
| > paragraph (d)(3) of    | > required in      | > Worth Airplane    |
| > this AD. The Office of | > paragraph (d)(3) | > Certification     |
| > Management and Budget  | > of this AD or    | > Office, 2601      |
| > (OMB) approved the     | > within 10 days   | > Meacham           |
| > information collection | > after June 14,   | > Boulevard, Fort   |
| > requirements contained | > 2002 (the        | > Worth, Texas      |
| > in this regulation     | > effective date   | > 76193--0150;      |
| > under the provisions   | > of this AD,      | > telephone: (817)  |
| > of the Paperwork       | > whichever occurs | > 222--5102;        |
| > Reduction Act of 1980  | > later.           | > facsimile: (817)  |
| > (44 U.S.C. 3501 *et    |                    | > 222--5960.        |
| > seq.*) and assigned    |                    |                     |
| > OMB Control Number     |                    |                     |
| > 2120--0056.            |                    |                     |
+--------------------------+--------------------+---------------------+

BILLING CODE 4910--13--P

![](media/image2.png){width="6.798611111111111in"
height="7.428472222222222in"}

BILLING CODE 4910--13--C

\(e\) *Can I comply with this AD in any other way?*

\(1\) You may use an alternative method of compliance or adjust the
compliance time if:

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

\(ii\) The Manager, Fort Worth or Los Angeles Airplane Certification
Office (ACO), as applicable, approves your alternative. Submit your
request through an FAA Principal Maintenance Inspector. The inspector
may add comments before sending it to the Manager, Fort Worth or Los
Angeles ACO.

\(2\) Alternative methods of compliance approved for AD 2001--10--04
and/or AD 2000--14--51 are not considered approved for this AD.

\(3\) Alternative methods of compliance approved for AD 2001--10--04 R1
are considered approved for this AD.

**Note:** This AD applies to each airplane identified in paragraphs
(a)(1) and (a)(3) 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.

\(f\) *Are there any alternative methods of compliance already approved
or being considered for this AD?* The FAA may approve, as an alternative
method of compliance, inspection of the wing lower spar cap. You must
submit the request in accordance with the procedures in paragraph (e) of
this AD and adhere to the following:

\(1\) If you are over or within 50 hours TIS of the safe life for the
wing lower spar cap and you have ordered parts and scheduled a date for
the replacement/modification, but having the replacement/modification
done on this date grounds the airplane, accomplish the following:

\(i\) inspect the wing lower spar cap within 50 hours TIS after approval
of the alternative method of compliance;

\(ii\) reinspect thereafter at intervals not to exceed 400 hours TIS
until either cracks are found, the date of the scheduled
replacement/modification occurs, or 1,200 hours TIS after the initial
inspection are accumulated, whichever occurs first; and

\(iii\) accomplish the inspections in accordance with the procedures in
Snow Engineering Service Letter &num;197 or &num;205, both Revised March
26, 2001, as applicable.

\(2\) Submit the following to the Fort Worth or Los Angeles ACO, as
applicable, using the procedures described in paragraph (e) of this AD:

\(i\) the airplane model serial number designation, and airplane
registration number (N-number);

\(ii\) the number of hours TIS on the airplane;

\(iii\) the scheduled date for the replacement/modification; and

\(iv\) the name and location of the authorized repair shop.

\(3\) For more information about this issue, contact:

\(i\) For the airplanes that do not incorporate and never have
incorporated Marburger Enterprises, Inc. winglets: Rob Romero, Aerospace
Engineer, FAA, Fort Worth Airplane Certification Office, 2601 Meacham
Boulevard, Fort Worth, Texas 76193--0150; telephone: (817) 222--5102;
facsimile: (817) 222--5960; and

\(ii\) For the airplanes that incorporate or have incorporated winglets:
John Cecil, Aerospace Engineer, Los Angeles Aircraft Certification
Office, FAA, 3960 Paramount Boulevard, Lakewood, California 90712;
telephone: (562) 627-5228; facsimile: (562) 627--5210.

\(g\) *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 provided that the following is adhered to:

\(1\) Only operate in day visual flight rules (VFR) only.

\(2\) Ensure that the hopper is empty.

\(3\) Limit airspeed to 135 miles per hour (mph) indicated airspeed
(IAS).

\(4\) Avoid any unnecessary g-forces.

\(5\) Avoid areas of turbulence.

\(6\) Plan the flight to follow the most direct route.

\(h\) *Are any service bulletins incorporated into this AD by
reference?* Replacement and inspection actions required by this AD must
be done in accordance with Snow Engineering Service Letter #197 or #205,
both Revised March 26, 2001, as applicable. The Director of the Federal
Register previously approved this incorporation by reference under 5
U.S.C. 552(a) and 1 CFR part 51, as of June 8, 2001 (66 FR 27014, May
16, 2001). You can get copies from Air Tractor, Incorporated, P.O. Box
485, Olney, Texas 76374; or Marburger Enterprises, Inc., 1227 Hillcourt,
Williston, North Dakota 58801. You may view copies at 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 June 14, 2002.

**APPENDIX TO AD 2002--11--03**

The following provides procedures for determining the safe life for
Models AT--502, AT--502A, and AT--502B airplanes that incorporate or
have incorporated Marburger Enterprises, Inc. winglets. These winglets
are installed in accordance with Supplemental Type Certificate (STC)
SA00490LA.

**What If I Removed the Marburger Winglets Prior to Further Flight After
the Effective Date of This AD or Prior to the Effective Date of This
AD?**

1\. Review your airplane\'s logbook to determine your airplane\'s
time-in-service (TIS) with winglets installed per Marburger Enterprises
STC SA00490LA. This includes all time spent with the winglets currently
installed and any previous installations where the winglet was installed
and later removed.

*Example:* A review of your airplane\'s logbook shows that you have
accumulated 350 hours TIS since incorporating the Marburger STC. Further
review of the airplane\'s logbook shows that a previous owner had
installed the STC and later removed the winglets after accumulating 150
hours TIS. Therefore, your airplane\'s TIS with the winglets installed
is 500 hours.

If you determine that the winglet STC has never been incorporated on
your airplane, then your safe life is presented in paragraph (a)(1) of
this AD. Any future winglet installation will be subject to a reduced
safe life per these instructions.

2\. Determine your airplane\'s unmodified safe life from paragraph
(a)(1) of this AD.

*Example:* Your airplane is a Model AT--502B, serial number 0292. From
paragraph (a)(1) of this AD, the safe life of your airplane is 2,050
hours TIS.

All examples from hereon will be based on the Model AT--502B, serial
number 0292 airplane.

3\. Determine the winglet usage factor from paragraph (a)(3) of this AD.

*Example:* Again, your airplane is a Model AT--502B, serial number 0292.
From paragraph (a)(3) of this AD, your winglet usage factor is 1.2.

4\. Adjust the winglet TIS to account for the winglet usage factor.
Multiply the winglet TIS (result of Step 1 above) by the winglet usage
factor (result of Step 3 above).

*Example:* Winglet TIS is 500 hours X a winglet usage factor of 1.2. The
adjusted winglet TIS is 600 hours.

5\. Calculate the winglet usage penalty. Subtract the winglet TIS
(result of Step 1 above) from the adjusted winglet TIS (result of Step 4
above).

*Example:*  

![](media/image3.png){width="4.45in" height="0.5326388888888889in"}

6\. Adjust the safe life of your airplane to account for winglet usage.
Subtract the winglet usage penalty (result of Step 5 above) result from
the unmodified safe life from paragraph (a)(1) of this AD (result of
Step 2 above).

*Example:*  

![](media/image4.png){width="4.35in" height="0.5180555555555556in"}

7\. If you remove the winglets from your airplane prior to further
flight or no longer have the winglets installed on your airplane, the
safe life of your airplane is the adjusted safe life (result of Step 6
above). Enter this number in paragraph (d)(1)(i) of this AD and the
airplane logbook.

**What If I Have the Marburger Winglet Installed as of the Effective
Date of This AD and Plan to Operate My Airplane Without Removing the
Winglet?**

1\. Review your airplane\'s logbook to determine your airplane\'s TIS
without the winglets installed.

*Example:* A review of your airplane\'s logbook shows that you have
accumulated 1,500 hours TIS, including 500 hours with the Marburger
winglets installed. Therefore, your airplane\'s TIS without the winglets
installed is 1,000 hours.

2\. Determine your airplane\'s unmodified safe life from paragraph
(a)(1) of this AD.

*Example:* Your airplane is a Model AT--502B, serial number 0292. From
paragraph (a)(1) of this AD, the safe life of your airplane is 2,050
hours TIS.

All examples from hereon will be based on the Model AT--502B, serial
number 0292 airplane.

3\. Determine the winglet usage factor from paragraph (a)(3) of this AD.

*Example:* Again, your airplane is a Model AT--502B, serial number 0292.
From paragraph (a)(3) of this AD, your winglet usage factor is 1.2.

4\. Determine the potential winglet TIS. Subtract the TIS without the
winglets installed (result of Step 1 above) from the unmodified safe
life (result of Step 2 above).

*Example:*

![](media/image5.png){width="4.6in" height="0.4861111111111111in"}

5\. Adjust the potential winglet TIS to account for the winglet usage
factor. Divide the potential winglet TIS (result of Step 4 above) by the
winglet usage factor (result of Step 3 above).

![](media/image6.png){width="5.2in" height="0.4986111111111111in"}
*Example:*  

6\. Calculate the winglet usage penalty. Subtract the adjusted potential
winglet TIS (result of Step 5 above) from the potential winglet TIS
(result of Step 4 above).

![](media/image7.png){width="5.3in" height="0.48194444444444445in"}
*Example:*

7\. Adjust the safe life of your airplane to account for the winglet
installation. Subtract the winglet usage penalty (result of Step 6
above) from the unmodified safe life from paragraph (a)(1) of this AD
(result of Step 2 above).

![](media/image8.png){width="4.8in" height="0.5319444444444444in"}
*Example:*

8\. Enter the adjusted safe life (result of Step 7 above) in paragraph
(d)(1)(i) of this AD and the airplane logbook.

**What If I Install or Remove the Marburger Winglet From My Airplane in
the Future?**

If, at anytime in the future, you install or remove the Marburger
winglet STC from your airplane, you must repeat the procedures in this
Appendix to determine the airplane\'s safe life.

**FOR FURTHER INFORMATION CONTACT:** Direct all questions to:

For the airplanes that do not incorporate and never have incorporated
Marburger Enterprises, Inc. winglets: Rob Romero, Aerospace Engineer,
FAA, Fort Worth Airplane Certification Office, 2601 Meacham Boulevard,
Fort Worth, Texas 76193--0150; telephone: (817) 222--5102; facsimile:
(817) 222--5960; and

For airplanes that incorporate or have incorporated Marburger
Enterprises, Inc. winglets: John Cecil, Aerospace Engineer, Los Angeles
Aircraft Certification Office, FAA, 3960 Paramount Boulevard, Lakewood,
California 90712; telephone: (562) 627--5228; facsimile: (562)
627--5210.

Issued in Kansas City, Missouri, on May 22, 2002.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02--13423 Filed 6--3--02; 8:45 am\]

BILLING CODE 4910--13--P

**BW 2002-12**

**RAYTHEON AIRCRAFT COMPANY**

**AIRWORTHINESS DIRECTIVE**

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

**2002-11-07 Raytheon Aircraft Company:** Amendment 39-12768; Docket No.
2001-CE-43-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:

+-------------------+--------------------------------------------------+
| > **Model**       | > **Serial Nos.**                                |
+-------------------+--------------------------------------------------+
| > E55 and E55A    | > TE--768 through TE--1201.                      |
+-------------------+--------------------------------------------------+
| > A56TC           | > TG--84 through TG--94.                         |
+-------------------+--------------------------------------------------+
| > 58 and 58A      | > TH--1 through TH--1388 and TH--1390 through    |
|                   | > TH--1395.                                      |
+-------------------+--------------------------------------------------+
| > 58P and 58PA    | > TJ--3 through TJ--435 and TJ--437 through      |
|                   | > TJ--443.                                       |
+-------------------+--------------------------------------------------+
| > 58TC and 58TCA  | > TK--1 through TK--146 and TK--148 through      |
|                   | > TK--150.                                       |
+-------------------+--------------------------------------------------+

\(b\) *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 damage to the rotating beacon circuit breaker
switch or any other switch in the same location because of an incorrect
length electroluminescent panel retaining screw. This condition could
result in failure of the circuit breaker and lead to smoke and/or fire
in the cockpit.

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

+-----------------------------------+----------------+-----------------+
| > **Actions**                     | >              | >               |
|                                   | **Compliance** |  **Procedures** |
+-----------------------------------+----------------+-----------------+
| > \(1\) Inspect the Instrument    | > Within the   | > In accordance |
| > Subpanel electroluminescent     | > next 100     | > with the      |
| > panel for the installation of a | > hours        | >               |
| > rotating beacon circuit breaker | > t            |  Accomplishment |
| > switch or any other switch      | ime-in-service | > Instructions  |
| > directly above the lower        | > (TIS) after  | > section of    |
| > electroluminescent panel        | > July 15,     | > Raytheon      |
| > retaining screw.\               | > 2002 (the    | > Mandatory     |
| > (i) If a blanking plug is       | > effective    | > Service       |
| > installed above the lower       | > date of this | > Bulletin SB   |
| > electroluminescent panel        | > AD).         | > 33--3452,     |
| > retaining screw, ensure that    |                | > Issued: May,  |
| > the correct length screw is     |                | > 2001.         |
| > installed. The correct length   |                |                 |
| > is 0.28 to 0.31 inches\         |                |                 |
| > (ii) If the screw is not the    |                |                 |
| > correct length, install part    |                |                 |
| > number (P/N) MS35214--24 or     |                |                 |
| > FAA-approved equivalent part    |                |                 |
| > number\                         |                |                 |
| > (iii) If a rotating beacon      |                |                 |
| > circuit breaker switch or any   |                |                 |
| > other switch is installed,      |                |                 |
| > inspect the switch for damage.  |                |                 |
+-----------------------------------+----------------+-----------------+
| > \(2\) Replace any damaged       | > Prior to     | > In accordance |
| > switch found during the         | > further      | > with the      |
| > inspection required in          | > flight after | >               |
| > paragraph (d)(1)(iii) of this   | > the          |  Accomplishment |
| > AD and replace the              | > inspection   | > Instructions  |
| > electroluminescent panel        | > required by  | > section of    |
| > retaining screw if it is not    | > paragraph    | > Raytheon      |
| > 0.28 to 0.31 inches in length   | > (d)(1)(iii)  | > Mandatory     |
| > with a P/N MS35214--24 screw or | > of this AD.  | > Service       |
| > FAA-approved equivalent part    |                | > Bulletin SB   |
| > number.                         |                | > 33--3452,     |
|                                   |                | > Issued: May,  |
|                                   |                | > 2001.         |
+-----------------------------------+----------------+-----------------+
| > \(3\) Do not install any        | > As of July   | > Not           |
| > electroluminescent panel        | > 15, 2002     | > applicable.   |
| > retaining screw in the lower    | > (the         |                 |
| > part of the Instrument Subpanel | > effective    |                 |
| > (underneath the circuit breaker | > date of this |                 |
| > switches) that is not P/N       | > AD).         |                 |
| > MS35214--24 or FAA-approved     |                |                 |
| > equivalent part number.         |                |                 |
+-----------------------------------+----------------+-----------------+

\(e\) *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:** 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 Todd Dixon, Aerospace
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road,
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316)
946-4152; facsimile: (316) 946-4407.

\(g\) *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
Raytheon Mandatory Service Bulletin SB 33-3452, Issued: May, 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 Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085.
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 July 15, 2002.

**FOR FURTHER INFORMATION CONTACT:** Todd Dixon, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100,
Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4152;
facsimile: (316) 946-4407.

Issued in Kansas City, Missouri, on May 23, 2002.

James E. Jackson,

Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-13764 Filed 6-5-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**BELL HELICOPTER TEXTRON CANADA**

**AIRWORTHINESS DIRECTIVE**

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

**2002-11-09 Bell Helicopter Textron Canada:** Amendment 39-12770.
Docket No. 2001-SW-54-AD.

**Applicability:** Model 407 helicopters, serial number 53000 through
53442, with flywheel, part number (P/N) 407-040-316-101, 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 (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 as indicated, unless accomplished previously.

To detect a crack in the forward bearing hanger bracket (bracket) and to
prevent loss of tail rotor drive or tail rotor control and subsequent
loss of control of the helicopter, accomplish the following:

\(a\) Within 25 hours time-in-service (TIS) and thereafter at intervals
not to exceed 25 hours TIS, visually inspect each bracket, P/N
407-040-321-101 or -103, for a crack in the shaded area shown in Figure
1 of this AD. Remove any cracked bracket from service.

**Note 2:** Dismantling of the bearing hanger and the support is not
required to accomplish the requirements of this AD.

![](media/image9.png){width="5.95in" height="4.5368055555555555in"}

**Note 3:** Bell Helicopter Textron Canada Alert Service Bulletin No.
407-01-39, Revision A, dated May 30, 2001, pertains to the subject of
this AD.

\(b\) 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 4:** 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 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.

\(d\) This amendment becomes effective on July 16, 2002.

**Note 5:** The subject of this AD is addressed in Transport Canada
(Canada) AD No. CF-2001-32, dated August 13, 2001.

**FOR FURTHER INFORMATION CONTACT:** Sharon Miles, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations Group, Fort Worth,
Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961.

Issued in Fort Worth, Texas, on May 28, 2002.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02-14566 Filed 6-10-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**SIKORSKY AIRCRAFT CORPORATION**

**AIRWORTHINESS DIRECTIVE**

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

**2002-11-10 Sikorsky Aircraft Corporation:** Amendment 39-12771. Docket
No. 2002-SW-10-AD. Supersedes AD 2001-25-08, Amendment 39-12561, Docket
No. 2001-SW-18-AD.

**Applicability:** Model S-70A helicopters, serial numbers (S/N) 700029,
701129, 701322, 701325, 701327, 701329, 701331, 701333, 701592, 701593,
701594, 701595, 701613, 701614, 701825, 701835, 702127, and 702129, and
Model S-70C helicopters, S/N 70583, 70785, 70788, 70792, 70793, 70794,
70797, 70798, 70799, 70800, 70811, 70812, 70813, 70830, 70831, 70836,
70837, 70848, 70855, 70856, 70867, 70868, 70879, 70884, 70892, 70910,
70918, 70927, 70928, 70929, 70949, 70950, 70951, 70954, 70957, 70958,
70959, 70965, 70966, and 701029, 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 within 30 hours time-in-service, unless
accomplished previously.

To prevent excessive torque on a jackpad mounting bolt retention nut
(nut), failure of a main landing gear drag beam (beam), and subsequent
loss of control of the helicopter during takeoff or landing, accomplish
the following:

\(a\) With jackpad installed, using a 10X or higher magnifying glass,
visually inspect each beam, part number (P/N) 70250-12105 or
70250-32105, for a crack at a 3.0-inch radius around the upper and lower
jackpad holes.

\(1\) If a crack is found, remove the beam.

\(2\) If a crack is suspected, dye-penetrant inspect the beam, and if a
crack is found, remove the beam.

**Note 2:** Temporary Revision No. 19 of Sikorsky Aircraft Model S-70
Maintenance Manual, dated January 23, 2001, pertains to the subject of
this AD.

\(b\) If a crack is not found while accomplishing the requirements of
paragraph (a) of this AD, retorque the nut, P/N MS21245-L12, on each
beam as follows:

\(1\) Restrain the jackpad and rotate the nut counterclockwise to
release the torque on the nut. If movement of the jackpad occurs, remove
and replace the sealant from the lower surface of the jackpad/beam
interface.

\(2\) Retorque the nut to 45-50 ft-lbs.

\(3\) Apply sealant to the nut and the immediate area.

\(4\) After sealant has dried, touch up the paint as required.

\(5\) After the paint has dried, apply a slippage mark (of a contrasting
color) to the nut as follows:

\(i\) Wipe the area to be marked with a clean-lint-free cloth.

\(ii\) Apply F1000 Sentry Seal, or equivalent, with a width of
approximately one half the diameter of the nut (to a maximum width of
3/16 inch) and extending a minimum of 1/2 inch on the base part (or to
the edge of the part, whichever is smaller).

**Note 3:** Sikorsky Alert Service Bulletin No. 70-03-2, dated July 26,
1999, pertains to the subject of this AD.

\(c\) 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, Boston Aircraft Certification Office, FAA.
Operators shall submit their requests through an FAA Principal
Inspector, who may concur or comment and then send it to the Manager,
Boston Aircraft Certification Office.

**Note 4:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
Boston Aircraft 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 June 24, 2002.

**FOR FURTHER INFORMATION CONTACT:** Terry Fahr, Aviation Safety
Engineer, Boston Aircraft Certification Office, 12 New England Executive
Park, Burlington, MA 01803, telephone (781) 238-7155, fax (781)
238-7199.

Issued in Fort Worth, Texas, on May 28, 2002.

David A. Downey,

Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02-14249 Filed 6-6-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**EUROCOPTER FRANCE**

**AIRWORTHINESS DIRECTIVE**

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

**2002--12--02** **Eurocopter France:** Amendment 39--12774. Docket No.
2001--SW--60--AD.

**Applicability:** Model AS332L2 helicopters, with engine fire
extinguishing bottle (bottle), part number (P/N) 862690--00, installed,
certificated in any category.

**Note 1:** Bottles with "Amendment A" noted on the bottle\'s indicating
label (label) are not subject to the applicability of this AD.

**Note 2:** 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:** Before further flight, unless accomplished previously.

To prevent release of the fire-extinguishing agent into the wrong engine
compartment, failure to extinguish a fire, and subsequent loss of
control of the helicopter, accomplish the following:

\(a\) Visually inspect each bottle for correct connection to the bottle
percussion heads and attachment cartridges in accordance with the
Accomplishment Instructions, paragraphs 2.B.1. through 2.B.2.2., of
Eurocopter France Alert Telex No. 26.00.12, dated October 3, 2001
(Telex).

\(1\) If the percussion heads and attachment cartridges are connected to
the bottle correctly, record "Amendment A" on the bottle\'s label and on
the Equipment Log Card (FME) of the bottle, close the sliding cowling,
and remove the access equipment.

\(2\) If the percussion heads and the attachment cartridges are not
connected to the bottle correctly, reconfigure each bottle in accordance
with the Accomplishment Instructions, paragraphs 2.B.4. through
2.B.4.4., of the Telex.

\(b\) Before installing, inspect any spare bottle to ensure that the
yellow percussion head is located below the pressure gage and that the
gray percussion head is located opposite the pressure gage.

\(1\) If the percussion heads are properly located, record "Amendment A"
on the bottle\'s label and on the FME of the bottle.

\(2\) If the percussion heads are not located properly, loosen the union
nuts; appropriately interchange the percussion heads, tighten the union
nuts by hand, and record "Amendment A" on the label and on the FME of
the bottle.

\(c\) 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, 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 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
Regulations Group.

\(d\) 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.

\(e\) The inspections and modifications shall be done in accordance with
the Accomplishment Instructions, paragraphs 2.B.1. through 2.B.2.2., and
paragraphs 2.B.4 through 2.B.4.4., of Eurocopter France Alert Telex No.
26.00.12, dated October 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 American
Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas
75053--4005, telephone (972) 641--3460, fax (972) 641--3527. 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.

\(f\) This amendment becomes effective on June 27, 2002.

**Note 4:** The subject of this AD is addressed in Direction Generale De
L\'Aviation Civile (France) AD T2001--471--020(A), dated October 5,
2001.

**FOR FURTHER INFORMATION CONTACT:** Ed Cuevas, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations Group, Fort Worth,
Texas 76193--0111, telephone (817) 222--5355 fax (817) 222--5961.

Issued in Fort Worth, Texas, on May 31, 2002.

David A. Downey,

Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02--14568 Filed 6--11--02; 8:45 am\]

BILLING CODE 4910--13--P

**BW 2002-12**

**EUROCOPTER FRANCE**

**AIRWORTHINESS DIRECTIVE**

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

**Corrected Copy:** *The effective date listed in paragraph (g) of this
AD is incorrect. The correct effective date, as shown in the DATES
portion of the AD, is June 27, 2002. The FAA and the Office of the
Federal Register will issue a correction. This copy reflects the
correction.*

**2002--12--03 Eurocopter France:** Amendment 39--12775. Docket No.
2001--SW--63--AD.

**Applicability:** Model AS332L2 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 (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 friction on the main rotor shaft non-rotating scissors
(non-rotating scissors), failure of the swashplate, loss of main rotor
pitch control, and subsequent loss of control of the helicopter,
accomplish the following:

\(a\) For non-rotating scissors with less than 275 hours time-in-service
(TIS), before reaching 275 hours TIS and then at intervals not to exceed
275 hours TIS, remove the non-rotating scissors from the swashplate
balljoint and inspect for any friction or play in accordance with
paragraph 2.B.1 of the Accomplishment Instructions in Eurocopter Alert
Service Bulletin No. 05.00.56, dated February 1, 2001 (ASB).

\(b\) For non-rotating scissors with 275 or more hours TIS, within 50
hours TIS and then at intervals not to exceed 275 hours TIS, remove the
non-rotating scissors from the swashplate balljoint and inspect for
friction or play in accordance with paragraph 2.B.1 of the
Accomplishment Instructions in the ASB.

\(c\) If friction or play is present, replace the non-rotating scissors
with airworthy parts.

\(d\) 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, Rotorcraft Directorate.
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
requirements of this AD can be accomplished.

\(f\) The inspections and replacement (if replacement is necessary)
shall be done in accordance with the Accomplishment Instructions,
paragraph 2.B.1 of Eurocopter Alert Service Bulletin No. 05.00.56, dated
February 1, 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 American Eurocopter
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053--4005,
telephone (972) 641--3460, fax (972) 641--3527. 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.

\(g\) This amendment becomes effective on June 27, 2002.

**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 May 28, 2002.

David A. Downey,

Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02--14567 Filed 6--11--02; 8:45 am\]

BILLING CODE 4910--13--P