**FEDERAL AVIATION ADMINISTRATION**

**AIRWORTHINESS DIRECTIVES**

**SMALL AIRCRAFT, ROTORCRAFT, GLIDERS,**

**BALLOONS, & AIRSHIPS**

**BIWEEKLY 2002-11**

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

**BW 2002-11**

**RAYTHEON AIRCRAFT COMPANY**

**AIRWORTHINESS DIRECTIVE**

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

**2002-10-13 Raytheon Aircraft Company:** Amendment 39-12759; Docket No.
2001-CE-32-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 numbers**                           |
+---------------------+------------------------------------------------+
| > 58P               | > TJ--3 through TJ--497.                       |
+---------------------+------------------------------------------------+
| > 60                | > P--4 through P--122 and P--124 through       |
|                     | > P--126.                                      |
+---------------------+------------------------------------------------+
| > A60               | > P--123 and P--127 through P--246.            |
+---------------------+------------------------------------------------+
| > B60               | > P--247 through P--596.                       |
+---------------------+------------------------------------------------+
| > 65--88            | > LP--1 through LP--26, LP--28, and LP--30     |
|                     | > through LP--47.                              |
+---------------------+------------------------------------------------+

\(b\) *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 assure that clear and complete operating instructions
are visible for opening the exit doors. If not visible and
understandable, this could result in the inability to open the exit door
during an emergency situation.

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

+------------------+-----------------------------+---------------------+
| > **Actions**    | > **Compliance**            | > **Procedures**    |
+------------------+-----------------------------+---------------------+
| > Modify the     | > Within the next 100 hours | > In accordance     |
| > exterior door  | > time-in-service (TIS)     | > with the          |
| > operating      | > after July 8, 2002 (the   | > Accomplishment    |
| > procedures by  | > effective date of this    | > Instructions      |
| > installing the | > AD) or within the next 12 | > section of        |
| > applicable     | > calendar months after     | > Raytheon Aircraft |
| > placard as     | > July 8, 2002 (the         | > Mandatory Service |
| > specified in   | > effective date of this    | > Bulletin SB       |
| > the service    | > AD), whichever occurs     | > 11--3404, Issued: |
| > bulletin.      | > first, unless already     | > June, 2001.       |
|                  | > accomplished.             |                     |
+------------------+-----------------------------+---------------------+

\(e\) *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 Steven E. Potter, Aerospace
Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road,
Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4124;
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
Aircraft Mandatory Service Bulletin SB 11-3404, Issued: June, 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 8, 2002.

**FOR FURTHER INFORMATION CONTACT:** Steven E. Potter, Aerospace
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road,
Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4124;
facsimile: (316) 946-4407.

Issued in Kansas City, Missouri, on May 16, 2002.

Terry L. Chasteen,

Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-12885 Filed 5-23-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-11**

**BOMBARDIER-ROTAX GMBH**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

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

**2002-10-14 Bombardier-Rotax GmbH:** Amendment 39-12760. Docket No.
2002-NE-07-AD.

**Applicability**

This airworthiness directive (AD) is applicable to Bombardier-Rotax GmbH
914 F series reciprocating engines with exhaust bend assemblies part
numbers (P/N\'s) 979422, 979432, 979442, and 979452 installed. These
engines are installed on, but not limited to, Aeromot-Industria Mecanico
Metalurgica, AMT-300 (Turbo Ximango Shark), Diamond Aircraft Industries,
HK 36 TTS, HK 36 TTC, HK 36 TTC-ECO, and Stemme GmbH & Co. KG, S10--VT,
Series Powered Sailplanes.

**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 (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 as indicated, unless already done.

To prevent carbon monoxide from entering the cabin, and also to prevent
the possibility of an engine fire, do the following:

**Initial Inspection**

\(a\) Within 50 hours time-in-service (TIS) after the effective date of
this AD, visually inspect the exhaust bend assemblies (item 1, Figure 1,
of this AD), located between the cylinder heads and exhaust manifold
assembly, for exterior traces of smoke, cracks, and damage, especially
around the exhaust gas temperature (EGT) bosses (item 2). Replace any
exhaust bend assembly found cracked. Figure 1 follows:

![](media/image2.png){width="6.321527777777778in" height="7.1in"}

**Note 2:** Information concerning this inspection can be found in
Bombardier-Rotax service bulletin No. SB-914-017, dated May 2001.

**Repetitive Inspections**

\(b\) Thereafter, inspect the exhaust bend assemblies every additional
50 hours TIS. Replace any exhaust manifold assembly found cracked.

\(c\) If any exhaust bend assembly is replaced, perform a ground test
run and exhaust leakage test.

**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, 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 3:** 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**

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

**Note 4:** The subject of this AD is addressed in Austro Control
airworthiness directive No. 106, dated April 25, 2001.

**Effective Date**

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

**FOR FURTHER INFORMATION CONTACT:** James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299.

Issued in Burlington, Massachusetts, on May 16, 2002.

Peter A. White,

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

\[FR Doc. 02-13186 Filed 5-24-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-11**

**EUROCOPTER DEUTSCHLAND**

**AIRWORTHINESS DIRECTIVE**

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

**2002-11-01 Eurocopter Deutschland:** Amendment 39-12762. Docket No.
2001-SW-69-AD.

**Applicability:** Model EC135 helicopters with Turbomeca Arrius 2B1
engines installed, certificated in any category.

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

**Compliance:** Required within 50 hours time-in-service, unless
accomplished previously.

To prevent deactivation of the engine main fuel-metering valve, an
engine electrical control unit (FADEC) fail caution indication display
to the pilot, loss of automatic control of the affected engine, and
subsequent loss of control of the helicopter, accomplish the following:

\(a\) Modify the FADEC software in accordance with the Operating
Instructions, paragraph 2.B., of Turbomeca Service Bulletin No. 319 73
2019, dated March 26, 2001.

\(b\) Modify the collective linear transducers (LVDTs) in accordance
with the Accomplishment Instructions, paragraph 3.C., of Eurocopter
Alert Service Bulletin EC135-71A-019, dated August 30, 2001.

\(c\) 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 2:** 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 modifications shall be done in accordance with Eurocopter
Alert Service Bulletin No. EC135-71A-019, dated August 30, 2001, and
Turbomeca Service Bulletin No. 319 73 2019, dated March 26, 2001. These
incorporations by reference were 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; and Turbomeca, DSO/T/NORIA Arrius 2 B1 TU 19C, 64 511 Bordes
Cedex, France. 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 14, 2002.

**Note 3:** The subject of this AD is addressed in Luftfahrt-Bundesamt
(Federal Republic of Germany) AD 2001-304/2, dated October 19, 2001.

**FOR FURTHER INFORMATION CONTACT:** Paul Madej, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort
Worth, Texas 76193-0110, telephone (817) 222-5125, fax (817) 222-5961.

Issued in Fort Worth, Texas, on May 20, 2002.

David A. Downey,

Manager, Rotorcraft Directorate, Aircraft Certification Service.

\[FR Doc. 02-13290 Filed 5-29-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-11**

**RAYTHEON AIRCRAFT COMPANY**

**AIRWORTHINESS DIRECTIVE**

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

**2002-11-02 Raytheon Aircraft Company:** Amendment 39-12763; Docket No.
2002-CE-19-AD.

\(a\) *What airplanes are affected by this AD?* This AD applies to the
following airplanes that are certificated in any category:

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

  390                           RB-4 through RB-14, RB-20 through RB-22,
                                RB-24 through RB-32, and RB-34.
  ----------------------------- -----------------------------------------

\(b\) *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 ice formation on the wing leading edges and
the upper and lower wing surfaces during flight in icing conditions. Ice
formation on the wings could cause symmetric or asymmetric loss of lift,
degradation of handling qualities, and increased drag of the airplane.

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

+-----------------------+------------+---------------------------------+
| > **Actions**         | > **Co     | > **Procedures**                |
|                       | mpliance** |                                 |
+-----------------------+------------+---------------------------------+
| > Insert page 2       | > Within   | > Incorporating the AFM         |
| > (Limitations        | > the next | > revisions, as required by     |
| > Section) and page 3 | > 15       | > this AD, may be performed by  |
| > (Abnormal           | > calendar | > anyone who holds at least a   |
| > Procedures Section) | > days     | > private pilot certificate, as |
| > of Raytheon         | > after    | > authorized by section 43.7 of |
| > Temporary Change,   | > June 14, | > the Federal Aviation          |
| > Part Number (P/N)   | > 2002     | > Regulations (14 CFR 43.7. You |
| > 3                   | > (the     | > must make an entry into the   |
| 90--590001--0003BTC1, | >          | > aircraft records that shows   |
| > dated April 29,     |  effective | > compliance with this AD, in   |
| > 2002, into the      | > date of  | > accordance with section 43.9  |
| > FAA-approved        | > this     | > of the Federal Aviation       |
| > Airplane Flight     | > AD).     | > Regulations (14 CFR43.9).     |
| > Manual (AFM).       |            |                                 |
+-----------------------+------------+---------------------------------+

\(e\) *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 Paul DeVore, Aerospace
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road,
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316)
946-4142; 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.

\(h\) *When does this amendment become effective?* This amendment
becomes effective on June 14, 2002.

**FOR FURTHER INFORMATION CONTACT:** Paul DeVore, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100,
Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4142;
facsimile: (316) 946-4407.

Issued in Kansas City, Missouri, on May 20, 2002.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02-13289 Filed 5-28-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-11**

**AIR TRACTOR, INC.**

**AIRWORTHINESS DIRECTIVE**

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

**2002-11-05 Air Tractor, Inc.:** Amendment 39-12766; Docket No.
2001-CE-36-AD.

*(a) What airplanes are affected by this AD?* This AD applies to certain
Models AT-400, AT-401, AT-401B, AT-402, AT-402A, AT-402B, AT-501,
AT-802, and AT-802A airplanes. Use paragraph (a)(1) of this AD for
affected airplanes that do not incorporate and never have incorporated
winglets. Use paragraph (a)(3) of this AD for certain Models AT-401,
AT-401B, AT-402, AT-402A, AT-402B, and AT-501 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:

+---------+--------------------------------------------+---------------+
| > **    | > **Serial numbers**                       | > **Safe      |
| Model** |                                            | > life**      |
+---------+--------------------------------------------+---------------+
| >       | > all serial numbers beginning with 0416   | > 13,300      |
| AT--400 |                                            | > hours TIS.  |
+---------+--------------------------------------------+---------------+
| >       | > 0662 through 0951                        | > 10,757      |
| AT--401 |                                            | > hours TIS.  |
+---------+--------------------------------------------+---------------+
| > A     | > 0952 through 1014 and 1016 though 1020   | > 6,948 hours |
| T--401B |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| > A     | > 1015 and 1021 through 1124               | > 7,777 hours |
| T--401B |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| >       | > 0694 through 0951                        | > 7,440 hours |
| AT--402 |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| > A     | > 0738 through 0951                        | > 7,440 hours |
| T--402A |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| > A     | > 0952 through 1020                        | > 4,589 hours |
| T--402A |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| > A     | > 1021 through 1124                        | > 5,268 hours |
| T--402A |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| > A     | > 0966 through 1020                        | > 4,589 hours |
| T--402B |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| > A     | > 1021 through 1124                        | > 5,268 hours |
| T--402B |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| >       | > 0002 through 0061                        | > 4,531 hours |
| AT--501 |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| >       | > all serial numbers beginning with 0062   | > 7,693 hours |
| AT--501 |                                            | > TIS.        |
+---------+--------------------------------------------+---------------+
| >       | > 0001 through 0059 except those equipped  | > 4,132 hours |
| AT--802 | > with the factory-supplied part number    | > TIS.        |
|         | > 80540 computerized fire gate.            |               |
+---------+--------------------------------------------+---------------+
| >       | > 0060 through 0091 except those equipped  | > 4,188 hours |
| AT--802 | > with the factory-supplied part number    | > TIS.        |
|         | > 80540 computerized fire gate.            |               |
+---------+--------------------------------------------+---------------+
| >       | > 0092 through 0101 except those equipped  | > 8,163 hours |
| AT--802 | > with the factory-supplied part number    | > TIS.        |
|         | > 80540 computerized fire gate.            |               |
+---------+--------------------------------------------+---------------+
| > A     | > 0003 through 0059 except those equipped  | > 4,969 hours |
| T--802A | > with the factory-supplied part number    | > TIS.        |
|         | > 80540 computerized fire gate.            |               |
+---------+--------------------------------------------+---------------+
| > A     | > 0060 through 0091 except those equipped  | > 4,531 hours |
| T--802A | > with the factory-supplied part number    | > TIS.        |
|         | > 80540 computerized fire gate.            |               |
+---------+--------------------------------------------+---------------+
| > A     | > 0092 through 0101 except those equipped  | > 8,648 hours |
| T--802A | > with the factory-supplied part number    | > TIS.        |
|         | > 80540 computerized fire gate.            |               |
+---------+--------------------------------------------+---------------+

**Note 1:** This AD still applies to those airplanes that have converted
between fire fighting and agricultural dispersal.

\(2\) 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 in this paragraph, 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:

+------------+-------------------------------------+------------------+
| >          | > **Serial numbers**                | > **Winglet      |
|  **Model** |                                     | > usage factor** |
+------------+-------------------------------------+------------------+
| > AT-401   | > 0662 through 0951                 | > 1.6            |
+------------+-------------------------------------+------------------+
| > AT--401B | > 0952 through 1014 and 1016 though | > 1.1            |
|            | > 1020                              |                  |
+------------+-------------------------------------+------------------+
| > AT--401B | > 1015 and 1021 through 1124        | > 1.1            |
+------------+-------------------------------------+------------------+
| > AT--402  | > 0694 through 0951                 | > 1.6            |
+------------+-------------------------------------+------------------+
| > AT--402A | > 0738 through 0951                 | > 1.6            |
+------------+-------------------------------------+------------------+
| > AT--402A | > 0952 through 1020                 | > 1.1            |
+------------+-------------------------------------+------------------+
| > AT--402A | > 1021 through 1124                 | > 1.1            |
+------------+-------------------------------------+------------------+
| > AT--402B | > 0966 through 1020                 | > 1.1            |
+------------+-------------------------------------+------------------+
| > AT--402B | > 1021 through 1124                 | > 1.1            |
+------------+-------------------------------------+------------------+
| > AT--501  | > 0002 through 0061                 | > 1.6            |
+------------+-------------------------------------+------------------+
| > AT--501  | > all serial numbers beginning with | > 1.6            |
|            | > 0062                              |                  |
+------------+-------------------------------------+------------------+

\(b\) *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.

**Note 2:** The 10-hour TIS compliance time is maintained from AD
2001-10-04 R1.

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

+-----------------------------+-------------------+--------------------+
| **Actions**                 | **Compliance**    | **Procedures**     |
+-----------------------------+-------------------+--------------------+
| \(1\) Modify the applicable | Accomplish the    | The owner/operator |
| aircraft records (logbook)  | logbook entry     | holding at least a |
| as follows to show the      | within the next   | private pilot      |
| reduced safe life for the   | 10 hours TIS      | certificate as     |
| wing lower spar cap (use    | after July 12,    | authorized by      |
| the information from the    | 2002 (the         | section 43.7 of    |
| table in paragraph (a)(1)   | effective date of | the Federal        |
| of this AD and utilize the  | this AD).         | Aviation           |
| information in paragraph    |                   | Regulations (14    |
| (a)(3) of this AD and the   |                   | CFR 43.7) may      |
| Appendix to this AD, as     |                   | modify the         |
| applicable.                 |                   | aircraft records   |
|                             |                   | as specified in    |
|                             |                   | paragraphs         |
|                             |                   | (d)(1)(i) and      |
|                             |                   | (d)(1)(ii) of this |
|                             |                   | AD. Make an entry  |
|                             |                   | into the aircraft  |
|                             |                   | records showing    |
|                             |                   | compliance with    |
|                             |                   | this portion of    |
|                             |                   | the AD in          |
|                             |                   | accordance with    |
|                             |                   | section 43.9 of    |
|                             |                   | the Federal        |
|                             |                   | Aviation           |
|                             |                   | Regulations (14    |
|                             |                   | CFR 43.9).         |
|                             |                   | Accomplish the     |
|                             |                   | actual             |
|                             |                   | replac             |
|                             |                   | ement/modification |
|                             |                   | when the safe life |
|                             |                   | is reached in      |
|                             |                   | accordance with    |
|                             |                   | Snow Engineering   |
|                             |                   | Service Letter     |
|                             |                   | #202 or #203, both |
|                             |                   | Revised March 26,  |
|                             |                   | 2001, as           |
|                             |                   | applicable. The    |
|                             |                   | owner/operator may |
|                             |                   | not accomplish the |
|                             |                   | replace            |
|                             |                   | ment/modification, |
|                             |                   | unless he/she      |
|                             |                   | holds the proper   |
|                             |                   | mechanic           |
|                             |                   | authorization.     |
+-----------------------------+-------------------+--------------------+
| \(i\) For the affected      |                   |                    |
| Models AT--802 and AT--802A |                   |                    |
| airplanes: update the       |                   |                    |
| Owners Manual, Section      |                   |                    |
| 6---Airworthiness           |                   |                    |
| Limitations, Life Limited   |                   |                    |
| Parts.                      |                   |                    |
+-----------------------------+-------------------+--------------------+
| \(ii\) For all affected     |                   |                    |
| airplanes other than Models |                   |                    |
| AT--802 and AT--802A        |                   |                    |
| airplanes, incorporate the  |                   |                    |
| following into the Aircraft |                   |                    |
| Logbook: ''In accordance    |                   |                    |
| with this AD, 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) and the Appendix of  |                   |                    |
| this AD.                    |                   |                    |
+-----------------------------+-------------------+--------------------+
| \(iii\) If, as of the time  |                   |                    |
| of the logbook entry        |                   |                    |
| requirement of paragraph    |                   |                    |
| (d)(1) of this AD, your     |                   |                    |
| airplane is over or within  |                   |                    |
| 10 hours of the safe life,  |                   |                    |
| an additional 10 hours TIS  |                   |                    |
| is allowed to accomplish    |                   |                    |
| the                         |                   |                    |
| replacement/modification.   |                   |                    |
+-----------------------------+-------------------+--------------------+
| > \(2\) If you have ordered | > Inspect prior   | > In accordance    |
| > parts from the factory    | > to further      | > with the         |
| > when it is time to        | > flight after    | > procedures in    |
| > replace the wing lower    | > ordering the    | > Snow Engineering |
| > spar cap (as required     | > parts and       | > Service Letter   |
| > when you reach the        | > thereafter at   | > #202 or #203,    |
| > established safe life),   | > intervals not   | > both Revised     |
| > but the parts are not     | > to exceed 400   | > March 26, 2001,  |
| > available, you may        | > hours TIS until | > as applicable.   |
| > eddy-current inspect the  | > one of the      |                    |
| > wing lower spar cap.      | > criteria in     |                    |
| > These inspections are     | > Paragraphs      |                    |
| > allowed until one of the  | > (d)(2)(i),      |                    |
| > following occurs, at      | > (d)(2)(ii), and |                    |
| > which time the            | > (d)(2)(iii) of  |                    |
| > replacement/modification  | > this AD are     |                    |
| > must be accomplished:     | > met.            |                    |
+-----------------------------+-------------------+--------------------+
| > \(i\) 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      | > replace         | > procedures in    |
| > detect any crack before   | ment/modification | > Snow Engineering |
| > it extends to the         | > required when   | > Service Letter   |
| > modified center section   | > you reach the   | > #202 or #203,    |
| > of the wing and repair    | > new safe life.  | > both Revised     |
| > that crack or replace the | > For airplanes   | > March 26, 2001,  |
| > wing section. This        | > that had this   | > as applicable.   |
| > replacement must be       | > replace         |                    |
| > accomplished by a Level 2 | ment/modification |                    |
| > or Level 3 inspector that | > accomplished in |                    |
| > is certified for          | > accordance with |                    |
| > eddy-current inspection   | > either AD       |                    |
| > using the guidelines      | > 2001--10--04 or |                    |
| > established by the        | > AD 2001--10--04 |                    |
| > American Society for      | > R1, accomplish  |                    |
| > Nondestructive Testing or | > this inspection |                    |
| > MIL--STD--410. The        | > and any         |                    |
| > inspection must be        | > necessary       |                    |
| > accomplished by one of    | > corrective      |                    |
| > the following:            | > action within   |                    |
|                             | > the next 400    |                    |
|                             | > hours TIS after |                    |
|                             | > July 12, 2002   |                    |
|                             | > (the effective  |                    |
|                             | > date of this    |                    |
|                             | > AD), unless     |                    |
|                             | > already         |                    |
|                             | > accomplished    |                    |
|                             | > (have the       |                    |
|                             | > mechanic who    |                    |
|                             | > accomplished    |                    |
|                             | > the work mark   |                    |
|                             | > the logbook     |                    |
|                             | > 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.                |                   |                    |
+-----------------------------+-------------------+--------------------+

*(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 3:** 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 10 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 10 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 #202 or #203, 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 #202 or 203,
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 can look at 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.

\(i\) *Does this AD action affect any existing AD actions?* This
amendment supersedes AD 2001-10-04 R1, Amendment 39-12247.

\(j\) *When does this amendment become effective?* This amendment
becomes effective on July 12, 2002.

**Appendix to AD 2002-11-05**

The following provides procedures for determining the safe life for
those Models AT-401, AT-401B, AT-402, AT-402A, AT-402B, and AT-501
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-401B, serial number 1022. From
paragraph (a)(1) of this AD, the safe life of your airplane is 7,777
hours TIS.

All examples from hereon will be based on the Model AT-401B, serial
number 1022 airplane.

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

Example: Again, your airplane is a Model AT-401B, serial number 1022.
From paragraph (a)(3) of this AD, your winglet usage factor is 1.1.

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 1.1. The
adjusted winglet TIS is 550 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).

![](media/image3.png){width="4.385416666666667in"
height="0.4479166666666667in"}Example:

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.).

![](media/image4.png){width="4.375in"
height="0.5104166666666666in"}Example:

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)(ii) 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-401B, serial number 1022. From
paragraph (a)(1) of this AD, the safe life of your airplane is 7,777
hours TIS.

All examples from hereon will be based on the Model AT-401B, serial
number 1022 airplane.

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

Example: Again, your airplane is a Model AT-401B, serial number 1022.
From paragraph (a)(3) of this AD, your winglet usage factor is 1.1.

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).

![](media/image5.png){width="4.552083333333333in"
height="0.4895833333333333in"}Example:

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="5.239583333333333in"
height="0.5104166666666666in"}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="5.302083333333333in"
height="0.4895833333333333in"}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
(the result of Step 2 above).

![](media/image8.png){width="4.385416666666667in"
height="0.5104166666666666in"}

Example:

8\. Enter the adjusted safe life (result of Step 7 above) in paragraph
(d)(1)(ii) 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 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 certain Models AT-402, AT-402A, AT-402B, and AT-501 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 23, 2002.

James E. Jackson,

Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-13609 Filed 5-30-02; 8:45 am\]