![](media/image1.wmf){width="1.4013888888888888in"
height="1.3138888888888889in"}

# **FEDERAL AVIATION ADMINISTRATION**

## **AIRWORTHINESS DIRECTIVES**

**LARGE AIRCRAFT**

**BIWEEKLY 2002-15**

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

U.S. Department of Transportation

### Federal Aviation Administration

Regulatory Support Division

Delegation and Airworthiness Programs Branch, AIR-140

P. O. Box 26460

Oklahoma City, OK 73125-0460

FAX 405-954-4104

Biweekly 2002-01

  ------------ ---------- ----------------- ----------------------------------
  2001-23-12   R1         SAAB Aircraft     SAAB SF340A Series and SAAB 340B
                                            Series

  2001-23-15   C, S       Boeing            747 Series
               01-05-05                     

  2001-24-25   COR        McDonnell Douglas DC-9-10, -20, -30, -40 Series; and
                                            C-9

  2001-24-27   C, S       McDonnell Douglas DC-9-10, -20, -30, -40, -50
               96-02-05                     Series; DC-9-81, -82, -83, -87
                                            Series; MD-88; and C-9 Series

  2001-25-11   S 01-15-12 Pratt and Whitney Engine: PW4050, PW4052, PW4056,
               &\                           PW4060, PW4060A, PW4060C, PW4062,
               99-17-16                     PW4152, PW4156, PW4156A, PW4158,
                                            PW4160, PW4460, PW4462, and PW4650

  2001-26-11   S 00-24-26 Rolls-Royce       Engine: RB211 Trent 875, RB211
                                            Trent 877, RB211 Trent 884, RB211
                                            Trent 892, and RB211 Trent 892B
                                            Series

  2001-26-12   S 01-12-05 Boeing            747-100, 747-200, 747-300, and
                                            747SR Series

  2001-26-14   S 96-12-13 Dornier Luftfahrt 328-100

  2001-26-15              McDonnell Douglas DC-9-81, -82, -83, -87; and MD-88

  2001-26-16              McDonnell Douglas DC-9-81, -82, -83, -87 Series; and
                                            MD-88

  2001-26-17              Airbus Industrie  A330-202, -223, -243, -301, -321,
                                            -322, -323, -341, -342, and
                                            ‑343 Series

  2001-26-18              Dornier Luftfahrt 328-300 Series

  2001-26-19              Boeing            767 Series

  2001-26-20              Airbus Industrie  A319, A320, and A321 Series

  2001-26-21              Airbus Industrie  A319, A320, and A321 Series

  2001-26-22              BAE Systems       Avro 146-RJ Series
                          Limited           

  2001-26-23              Bombardier        DHC-8-102, -103, -106, -201, -202,
                                            -301, -311, and -315

  2001-26-24              McDonnell Douglas DC-9-10, -20, -30, -40, -50
                                            Series; and C-9

  2001-26-51   FR         Bombardier        CL-600-2B19 Series

  2002-01-03              GE Aircraft       Engine: CT7-5A2, -5A3, -7A, and
                                            -7A1
  ------------ ---------- ----------------- ----------------------------------

Biweekly 2002-02

  ------------ ---------- ----------------- ----------------------------------
  2002-01-01              Boeing            737-100, -200, -200C, -300, -400,
                                            and -500 Series

  2002-01-05              British Aerospace HP.137 Jetstream Mk.1, Jetstream
                                            Series 200, Jetstream Series 3101,
                                            and Jetstream Model 3201

  2002-01-08              Israel Aircraft   Galaxy
                          Industries        

  2002-01-12              General Electric  Engine: GE90-76B, -77B, -85B,
                          Company           -90B, and -94B

  2002-01-14   S 01-26-10 Airbus Industrie  A319, A320, and A321 Series

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

Biweekly 2002-03

+--------+---------+----------------+---------------------------------+
| 2001   | R1      | Raytheon       | DH.125, HS.125, BH.125, and     |
| -17-26 |         | Aircraft       | BAe.125 (U-125 and C-29A)       |
|        |         |                | Series, Hawker 800, Hawker 800  |
|        |         |                | (U-125A), Hawker 800XP, Hawker  |
|        |         |                | 1000                            |
+--------+---------+----------------+---------------------------------+
| 2001   | COR S   | McDonnell      | DC-9-10, -20, -30, -40, and -50 |
| -24-27 | 9       | Douglas        | Series; DC-9-81, -82, -83, and  |
|        | 6-02-05 |                | -87 Series,; MD-88; and C-9     |
|        |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2001   | COR     | Honeywell      | Engine: LTS101-600A-2 and       |
| -25-04 |         | International  | LTS101-600A-3 Turboshaft;       |
|        |         | Inc.           | LTP101-600A-1A and              |
|        |         |                | LTP101-700A-1A Turboprop        |
+--------+---------+----------------+---------------------------------+
| 2002   |         | General        | Engine: CF6-80E1                |
| -01-04 |         | Electric       |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Boeing         | 767 Series                      |
| -01-13 | 9       |                |                                 |
|        | 6-21-06 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 767-200, -300, and -300F Series |
| -01-15 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 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   |         | Dornier        | 328-100 Series                  |
| -01-17 |         | Luftfahrt      |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Airbus         | A319, A320, and A321 Series     |
| -01-18 |         | Industrie      |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Fokker         | F.28 Mark 0070 and 0100 Series  |
| -01-19 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | BAE Systems    | BAe 146-200A Series             |
| -01-20 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | BAE Systems    | BAe-146 Series and Avro 146-RJ  |
| -01-21 |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Short Brothers | SD3 Series                      |
| -01-22 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Raytheon       | Beech 400, Beech 400A, Beech    |
| -01-23 |         | Aircraft       | 400T Series, Beech 400T-1,      |
|        |         |                | Beech MU-300-10, Mitsubishi     |
|        |         |                | MU-300                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | DC-9-81, -82, , -83, and -87    |
| -01-24 |         | Douglas        | Series, and MD-88               |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Bombardier     | DHC-8-100, -200, and -300       |
| -01-25 |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Israel         | 1124 and 1124A Series, and 1125 |
| -01-26 |         | Aircraft       | Westwind Astra Series           |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | General        | Engine: GE90-76B, -77B, -85B,   |
| -01-27 | 9       | Electric       | and -90B Turbofan               |
|        | 8-15-03 | Company        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Dowty          | Propeller: R334/4-82-F/13       |
| -01-28 |         | Aerospace      |                                 |
+--------+---------+----------------+---------------------------------+

Biweekly 2002-03 cont\'d...

  ------------ ---------- ----------------- ----------------------------------
  2002-01-29              Rolls-Royce       Engine: Tay 650-15 and 651-54
                                            Turbofan

  2002-02-02              Boeing            707 and 720 Series

  2002-02-03              BAE Systems       BAe 146 Series

  2002-02-09              General Electric  Engine: CF6-45 and CF6-50 Series
                                            Turbofan

  2002-03-51   E          Hamilton          Propeller: 568F-1
                          Sundstrand        
  ------------ ---------- ----------------- ----------------------------------

Biweekly 2002-04

  ------------ ------------ ----------------- ----------------------------------
  2001-23-13   COR          Boeing            747 Series and 747SP Series

  2002-02-04                Boeing            757 Series

  2002-02-05                Airbus Industrie  A300 B2 and A300 B4; A300 B4-600,
                                              B4-600R, F4-600R (collectively
                                              called A300-600), and A310 Series

  2002-02-06                Airbus Industrie  A330-243, -341, -342, and -343
                                              Series

  2002-02-07                Airbus Industrie  A330 and A340 Series

  2002-02-08                Boeing            737-200, -200C, -300, and -500
                                              Series

  2002-02-12   S 2000-05-12 Rolls-Royce plc.  Engine: RB211-524G2-19,
                                              RB211-524G2-T-19, RB211-524G3-19,
                                              RB211-524G3-T-19, RB211-524H2-19,
                                              RB211-524H2-T-19, RB211-524H-36,
                                              and RB211-524H-T-36 Turbofan

  2002-02-13                CFM International Engine: CFM56-5 Series Turbofan

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

  2002-03-05                McDonnell Douglas DC-8 Series

  2002-03-06   S 2001-07-10 McDonnell Douglas DC-9-81, -82, -83, and -87 Series,
                                              MD-88, and MD-90-30 Series

  2002-03-07                BAE Systems       BAe 146 and Avro 146-RJ Series

  2002-03-08   S 2000-12-02 Pratt & Whitney   Engine: PW4050, PW4052, PW4056,
                                              PW4060, PW4060A, PW4060C, PW4062,
                                              PW4152, PW4156, PW4156A, PW4158,
                                              PW4160, PW4460, PW4462, PW4650,
                                              PW4164, PW4168, PW4168A, PW4074,
                                              PW4074D, PW4077, PW4077D, PW4084,
                                              PW4084D, PW4090, PW4090D, and
                                              PW4098 Turbofan

  2002-03-10                BAE Systems       BAe 146 Series and Avro 146-RJ
                                              Series

  2002-03-11   S 2000-11-27 Airbus Industrie  A319, A320, and A321 Series

  2002-03-12                Bombardier        DHC-8-400 Series

  2002-03-13                Short Brothers    SD3-60, SD3-60 SHERPA, and
                                              SD3-SHERPA Series

  2002-03-14                Bombardier        CL-600-2B19 Series

  2002-03-15                Dornier Luftfahrt 328-100 and 328-300 Series

  2002-04-01   S 97-02-10   McDonnell Douglas DC-9, DC-9-80, and C-9 Series;
                                              MD-88 and MD-90

  2002-04-02                Airbus Industrie  A300 F4-605R

  2002-04-03                Fokker            F27 Mark 050 Series

  2002-04-52   E, S         Hamilton          Propeller: 568F-1
               2002-03-51   Sundstrand        
  ------------ ------------ ----------------- ----------------------------------

Biweekly 2002-05

+--------+---------+----------------+---------------------------------+
| 2002   | COR     | Pratt &        | Engine: PW4050, PW4052, PW4056, |
| -03-08 |         | Whitney        | PW4060, PW4060A, PW4060C,       |
|        | S       |                | PW4062, PW4152, PW4156,         |
|        | 200     |                | PW4156A, PW4158, PW4160,        |
|        | 0-12-02 |                | PW4460, PW4462, PW4650, PW4164, |
|        |         |                | PW4168, PW4168A, PW4074,        |
|        |         |                | PW4074D, PW4077, PW4077D,       |
|        |         |                | PW4084, PW4084D, PW4090,        |
|        |         |                | PW4090-3, PW4090D, and PW4098   |
|        |         |                | Turbofan                        |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Airbus         | A300 B2-1C, A300 B2-203, A300   |
| -04-05 |         |                | B2K-3C, and A300 B4 Series,     |
|        |         |                | A300 B4-600 Series, A300        |
|        |         |                | B4-600R Series, A300 F4-605R,   |
|        |         |                | A310 Series                     |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 727 Series                      |
| -04-06 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 737-600, -700, -700C, and -800  |
| -04-08 |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | BAE Systems    | BAe 146 and Avro 146-RJ Series  |
| -04-09 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Airbus         | A319 Series and A320-200 Series |
| -04-10 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | General        | Engine: GE90-76B/ -77B/ -85B/   |
| -04-11 | 200     | Electric       | -90B/ -94B Series               |
|        | 0-08-10 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Boeing         | 747-100, 747-200, 747-300,      |
| -05-01 | 200     |                | 747SP, and 747SR Series         |
|        | 1-12-23 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | General        | Engine: CF34-3A1 and -3B1       |
| -05-02 | 200     | Electric       | Series Turbofan                 |
|        | 0-03-03 |                |                                 |
|        | R1      |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | General        | Engine: CF6-6, CF6-45, and      |
| -05-03 | 200     | Electric       | CF6-50 Series Turbofan          |
|        | 0-08-11 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | E,      | Hamilton       | Propeller: 568F-1               |
| -05-51 | S200    | Sundstrand     |                                 |
|        | 2-04-52 |                |                                 |
+--------+---------+----------------+---------------------------------+

Biweekly 2002-06

+--------+---------+----------------+---------------------------------+
| 2002   | COR     | Airbus         | A300 B2 and A300 B4; A300       |
| -02-05 |         |                | B4-600, B4-600R, and F4-600R    |
|        |         |                | (collectively called A300-600); |
|        |         |                | and Model A310 series           |
+--------+---------+----------------+---------------------------------+
| 2002   | COR,    | Rolls-Royce    | Engine: RB211-524G2-19,         |
| -02-12 |         | plc            | RB211-524G2-T-19,               |
|        | S       |                | RB211-524G3-19,                 |
|        | 200     |                | RB211-524G3-T-19,               |
|        | 0-05-12 |                | RB211-524H2-19,                 |
|        |         |                | RB211-524H2-T-19,               |
|        |         |                | RB211-524H-36, and              |
|        |         |                | RB211-524H-T-36 turbofan        |
+--------+---------+----------------+---------------------------------+
| 2002   | COR     | CFM            | Engine: CFM56-5 series turbofan |
| -02-13 |         | International  |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 737-100, -200, -200C, -300,     |
| -05-07 |         |                | -400, and -500 Series           |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 747 Series                      |
| -06-02 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 737-600, -700, -700C and -800   |
| -06-03 |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Transport      | Appliance: Mode C 621A-3 Air    |
| -06-05 |         | Category       | Traffic Control (ATC)           |
|        |         | Airplanes      | Transponder(s)                  |
|        |         |                |                                 |
|        |         | Rockwell       |                                 |
|        |         | Collins        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Airbus         | A300; A300 B4-600, B4-600R, and |
| -06-09 |         |                | F4-600R (collectively called    |
|        |         |                | A300-600); and A310 Series      |
+--------+---------+----------------+---------------------------------+
| 2002   | E       | Bombardier     | CL-600-2C10 (Regional Jet       |
| -06-51 |         |                | Series 700 and 701) Series      |
+--------+---------+----------------+---------------------------------+
| 2002   | E       | Airbus         | A319, A320, and A321, A330      |
| -06-53 |         |                | Series, A340 Series             |
+--------+---------+----------------+---------------------------------+

Biweekly 2002-07

+--------+---------+----------------+---------------------------------+
| 2002   |         | Rockwell       | Appliance: TDR-94 and TDR-94D   |
| -06-06 |         | Collins        | Mode S transponders             |
+--------+---------+----------------+---------------------------------+
| 2002   |         | General        | Engine: CF6-80E1 series         |
| -06-07 |         | Electric       | turbofan                        |
|        |         | Company        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-90-30                        |
| -06-11 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Dassault       | Mystere-Falcon 50 Series        |
| -06-12 |         | Aviation       |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-90-30                        |
| -06-13 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | DC-10-10, -10F, -15, -30, -30F  |
| -06-14 |         | Douglas        | (KC-10A and KDC-10), -40,       |
|        |         |                |                                 |
|        |         |                | and -40F series; and MD-10-10F  |
|        |         |                | and MD-10-30F Series            |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 777-200 and -300 Series         |
| -06-15 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 767-300                         |
| -06-16 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | FR      | Bombardier     | CL-600-2C10 (Regional Jet       |
| -06-51 |         |                | Series 700 and 701) Series      |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Israel         | Galaxy airplanes and Model      |
| -07-02 |         | Aircraft       | Gulfstream 200 Series           |
|        |         | Industries,    |                                 |
|        |         | Ltd.           |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Fokker         | F.28 Series                     |
| -07-03 |         | Services B.V.  |                                 |
+--------+---------+----------------+---------------------------------+

Biweekly 2002-08

  ------------ ------------ ----------------- ----------------------------------
  2002-07-04                Pratt & Whitney   Engine: JT9D-7R4D, -7R4D1, -7R4E,
                                              -7R4E1, -7R4E4, ‑7R4G2, and 7R4H1
                                              Series Turbofan

  2002-07-05                Airbus            A300 B2, A300 B4, A300 B4-600,
                                              A300 B4-600R Series, and A300
                                              F4-605R

  2002-07-06                McDonnell Douglas DC-9-10, -20, -30, -40, and -50
                                              Series, and C-9

  2002-07-07                Boeing            777-200 Series

  2002-07-08   S 97-22-07   Boeing            737-200, -200C, -300, -400, and
                                              -500 Series

  2002-07-09   S 99-04-22   Boeing            727 Series

  2002-07-10                Boeing            737-200, -200C, -300, -400, and
                                              -500 Series

  2002-07-11                Boeing            737-200 and -200C

  2002-07-12   S 2000-08-12 General Electric  Engine: CF6-80A, CF6-80C2, and
                                              CF6-80E1 Series Turbofan

  2002-08-01                Fairchild         SA226-AT, SA226-T, SA226-T(B),
                            Aircraft          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          SA226-TC, SA227-AC, SA227-AT,
                                              SA227-TT, and SA227-TT(300)

  2002-08-05                Bombardier        DHC-8-400, -401, and -402 Series

  2002-08-06                Boeing            777-200, -300 Series

  2002-08-07                Boeing            767-200, -300, and -300F Series

  2002-08-51   E            Airbus            A300 B2 and B4 Series

  2002-08-52   E            Boeing            737-600, -700, and -700C Series
  ------------ ------------ ----------------- ----------------------------------

Biweekly 2002-09

+--------+---------+----------------+---------------------------------+
| 2002   | COR, S  | General        | Engine: GE90-76B/ ‑77B/ -85B/   |
| -04-11 |         | Electric       | -90B/ -94B Series Turbofan      |
|        | 200     |                |                                 |
|        | 0-08-10 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Airbus         | A319, A320, and A321 Series     |
| -06-01 | 200     |                |                                 |
|        | 0-10-16 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | FR      | Airbus         | A319, A320, A321, A330, and     |
| -06-53 |         |                | A340 Series                     |
+--------+---------+----------------+---------------------------------+
| 2002   | COR, S  | Fairchild      | SA226-AT, SA226-T, SA226-T(B),  |
| -08-02 |         | Aircraft       | SA226-TC, SA227-AC, SA227-AT,   |
|        | 200     |                | SA227-TT, and SA227-TT(300)     |
|        | 1-20-14 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Bombardier     | CL-600-2B16 (CL-601-3R), and    |
| -08-08 |         |                | CL-600-2B16 (CL-604) Series     |
+--------+---------+----------------+---------------------------------+
| **Bi   |         |                |                                 |
| weekly |         |                |                                 |
| 2      |         |                |                                 |
| 002-09 |         |                |                                 |
| conti  |         |                |                                 |
| nued** |         |                |                                 |
+--------+---------+----------------+---------------------------------+
|        |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | DC-9-31                         |
| -08-09 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 747 Series                      |
| -08-10 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Pratt &        | Engine: JT9D-3A, -7, -7A, -7H,  |
| -08-11 | 200     | Whitney        | -7AH, -7F, -7J, -20, -20J,      |
|        | 0-01-13 |                | -59A, ‑70A, -7Q, -7Q3, -7R4D,   |
|        |         |                | -7R4D1, -7R4E, -7R4E1, -7R4E4,  |
|        |         |                | ‑7R4G2, and -7R4H1 Series       |
|        |         |                | Turbofan                        |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Airbus         | A330 and A340 Series            |
| -08-12 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Airbus         | A319, A320, and A321 Series     |
| -08-13 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Airbus         | A300 B2, B4, A300 B4-600,       |
| -08-14 |         |                | B4-600R, F4-600R (collectively  |
|        |         |                | called A300-600), and A310      |
|        |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 767 Series                      |
| -08-15 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | DC-10-10, DC-10-10F, DC-10-15,  |
| -08-17 |         | Douglas        | DC-10-30, DC-10-30F, and        |
|        |         |                | DC-10-30F (KC10A and KDC-10)    |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Embraer        | EMB-135 and -145 Series         |
| -08-18 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 737-600, -700, -700C, and -800  |
| -08-20 |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Embraer        | EMB-135 and -145 Series         |
| -08-21 | 200     |                |                                 |
|        | 1-17-04 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | FR      | Airbus         | A300 B2 and B4 Series           |
| -08-51 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | FR      | Boeing         | 737-600, -700, -700C Series     |
| -08-52 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Pratt &        | Engine: PW4090, PW4090-3,       |
| -09-01 |         | Whitney        | PW4074D, PW4077D, PW4090D, and  |
|        |         |                | PW4098 Turbofan                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Rolls-Royce,   | Engine: Tay 650-15 and 651-54   |
| -09-02 |         | plc            | Turbofan                        |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Bombardier     | CL-600-2B19 Series              |
| -09-05 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | DC-9-81 (MD-81), DC-9-82        |
| -09-06 |         | Douglas        | (MD-82), DC-9-83 (MD-83), and   |
|        |         |                | MD-88                           |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | DC-9-81 (MD-81), DC-9-82        |
| -09-07 |         | Douglas        | (MD-82), DC-9-83 (MD-83), and   |
|        |         |                | MD-88                           |
+--------+---------+----------------+---------------------------------+

**Biweekly 2002-10**

  ------------ ---------- ----------------- ----------------------------------
  2002-07-09   COR, S     Boeing            727 Series
               99-04-22                     

  2002-09-10              CFE Company       Engine: CFE738-1-1B Turbofan

  2002-10-01              McDonnell Douglas MD-90-30

  2002-10-02              Boeing            757 Series

  2002-10-03              McDonnell Douglas DC-9-81 (MD-81), DC-9-82 (MD-82),
                                            DC-9-83 (MD-83), DC-9-87 (MD‑87),
                                            MD-88, and Model MD-90-30

  2002-10-04              General Electric  Engine: CF6-80E1A2
                          Company           
  ------------ ---------- ----------------- ----------------------------------

**Biweekly 2002-11**

  ------------ ---------- ----------------- ----------------------------------
  2002-08-06   COR        Boeing            777-200 and -300 Series

  2002-10-06              Airbus            A319, A320, and A321 Series

  2002-10-07              Pratt & Whitney   Engine: JT9D-59A, -70A, -7Q, and
                                            -7Q3 Turbofan

  2002-10-08              General Electric  Engine: CF6-80E1 Series

  2002-10-09              Gulfstream        Galaxy and Gulfstream 200
                          Aerospace         

  2002-10-10   S 93-08-12 Boeing            747 Series

  2002-10-11   S 84-20-03 Boeing            737-100, -200, -200C, -300, -400,
               R1                           and -500 series

  2002-10-12              Boeing            737-100, -200, -200C, -300, -400,
                                            and -500 Series

  2002-10-15              Rolls-Royce plc   Engine: RB211 Trent 875, 877, 884,
                                            892, 892B, and 895 Series Turbofan
  ------------ ---------- ----------------- ----------------------------------

**Biweekly 2002-12**

  ------------ ------------ ----------------- ----------------------------------
  2002-08-19   S 2002-06-51 Bombardier        CL-600-2C10 (Regional Jet Series
                                              700 and 701) Series

  2002-11-04   S 97-16-06   Airbus            A300 B4-600, A300 B4-600R Series,
                                              and A300 F4-605R

  2002-11-06   S 2000-19-08 Boeing            777 Series

  2002-11-08                Rolls-Royce plc   Engine: RB211 Trent 875, 877, 884,
                                              892, 892B, and 895 series Turbofan

  2002-11-11                Boeing            767-200, -300, and -300F Series

  2002-12-01                BAe Systems       Jetstream 4101

  2002-12-05                Boeing            767 Series

  2002-12-06   S 2000-21-09 Pratt & Whitney   Engine: PW2037, PW2040, PW2037M,
                                              PW2240, PW2337, PW2043, PW2643,
                                              and PW2143 series Turbofan

  2002-12-08                Honeywell         Engine: ALF502 and LF507 Series
                            International     Turbofan
  ------------ ------------ ----------------- ----------------------------------

**Biweekly 2002-13**

+--------+---------+----------------+---------------------------------+
| 99     | R1      | CFE Company    | Engine: CFE738-1-1B turbofan    |
| -27-16 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | COR,    | General        | Engine: CF34-3A1 and -3B1       |
| -05-02 |         | Electric       | series turbofan                 |
|        | S       | Company        |                                 |
|        | 200     |                |                                 |
|        | 0-03-03 |                |                                 |
|        | R1      |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 757-200, 757-200CB, 757-200PF,  |
| -12-04 |         |                | 767-200, 767-300, and 767-300F  |
|        |         |                | series                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Honeywell      | Engine: TPE331-11U, -12B,       |
| -12-09 |         | International  | -12JR, ‑12UA, -12UAR, and       |
|        |         | Inc.           | -12UHR series turboprop         |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-90-30                        |
| -12-10 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Bombardier,    | DHC-8-100, -200 and --300       |
| -12-11 |         | Inc.           | series                          |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Bombardier,    | CL-215-1A10 and CL-215-6B11     |
| -12-12 | 9       | Inc.           | series                          |
|        | 9-16-04 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 727 series                      |
| -12-13 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Pratt &        | Engine: PW4052, PW4056, PW4060, |
| -12-15 | 200     | Whitney        | PW4062, PW4152, PW4156A,        |
|        | 1-20-13 |                | PW4158, PW4460, and PW4462      |
|        |         |                | turbofan                        |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-90-30                        |
| -13-01 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | CFM            | Engine: CFM56-2, -2A, ‑2B, -3,  |
| -13-03 | 200     | International  | -3B, -3C, -5, -5B, -5C, and -7B |
|        | 0-12-01 |                | series turbofan                 |
+--------+---------+----------------+---------------------------------+

**Biweekly 2002-14**

  ------------ ------------ ----------------- ----------------------------------
  2002-09-02   COR          Rolls-Royce, plc. Engine: Tay 650-15 and 651-54
                                              Turbofan

  2002-10-08   COR          General Electric  Engine: CF6-80E1 series Turbofan
                            Company           

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

  2002-13-09   S 2000-21-07 Pratt & Whitney   Engine: JT8D-200 series Turbofan

  2002-13-10                McDonnell Douglas DC-10-10, -10F, -15, -30, -30F,
                                              -30F (KC10A and KDC-10), -40,
                                              -40F, MD-10-10F, -30F, MD-11 and
                                              -11F

  2002-13-12   S 2001-24-15 McDonnell Douglas DC-9-10, -30, -30F, and -40
                                              series, and C-9

  2002-14-02                Boeing            767-300 series

  2002-14-16                McDonnell Douglas 717-200
  ------------ ------------ ----------------- ----------------------------------

**Biweekly 2002-15**

+--------+---------+----------------+---------------------------------+
| 2002   | COR     | Pratt &        | Engine: JT8D-200 Series         |
| -13-09 |         | Whitney        | Turbofan                        |
|        | S       |                |                                 |
|        | 200     |                |                                 |
|        | 0-21-07 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-03 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-04 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | McDonnell      | MD-11                           |
| -14-05 | 9       | Douglas        |                                 |
|        | 9-26-03 |                |                                 |
|        | C1      |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-06 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-07 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-08 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | McDonnell      | MD-11 and -11F                  |
| -14-09 | 200     | Douglas        |                                 |
|        | 0-03-15 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-10 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | McDonnell      | MD-11 and -11F                  |
| -14-11 | 200     | Douglas        |                                 |
|        | 0-24-13 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-12 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-13 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | MD-11 and -11F                  |
| -14-14 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | McDonnell      | MD-11 and -11F                  |
| -14-15 | 200     | Douglas        |                                 |
|        | 0-14-18 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Rockwell       | Appliance: Air Data Computers   |
| -14-19 |         | Collins        | (ADC)                           |
+--------+---------+----------------+---------------------------------+
| 2002   | COR     | Boeing         | 737-600, -700, -800, and -900   |
| -14-20 |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Boeing         | 737-600, -700, and -800 Series  |
| -14-21 | 9       |                |                                 |
|        | 9-03-08 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Embraer        | EMB-135 and -145 Series         |
| -14-23 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Cessna         | 650                             |
| -14-24 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Embraer        | EMB-135 and -145 Series         |
| -14-25 | 200     |                |                                 |
|        | 2-08-18 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Fokker         | F.28 Mark 0070, 0100, 1000,     |
| -14-27 | 9       |                | 2000, 3000, and 4000 Series     |
|        | 4-25-03 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Hamilton       | Appliance: Auxiliary Power      |
| -15-02 |         | Sundstrand     | Units (APU\'s)                  |
|        |         | Power Sys.     |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Hamilton       | Propellers: 568F-1              |
| -15-03 | 200     | Sundstrand     |                                 |
|        | 2-05-51 |                |                                 |
+--------+---------+----------------+---------------------------------+

**BW 2002-15**

**PRATT & WHITNEY**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**LARGE AIRCRAFT**

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

**AD 2002-13-09 Pratt & Whitney:** Amendment 39-12797. Docket No.
98ANE-43AD. Supersedes AD 2000-21-07, Amendment 39-11939.

**Applicability:** Pratt & Whitney (PW) JT8D-200 series turbofan
engines, installed on but not limited to McDonnell Douglas MD-80 series
airplanes.

**Note 1:** This airworthiness directive (AD) applies to each engine
identified in the preceding applicability provision, regardless of
whether it has been modified, altered, or repaired in the area subject
to the requirements of this AD. For engines that have been modified,
altered, or repaired so that the performance of the requirements of this
AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (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 as indicated, unless already done.

To prevent critical life-limited rotating engine part failure, which
could result in an uncontained engine failure and damage to the
airplane, do the following:

**Inspections**

\(a\) Within the next 30 days after the effective date of this AD,
revise the Time Limits Section (TLS) of the JT8D-200 Turbofan Engine
Manual, and for air carrier operations revise the approved continuous
airworthiness maintenance program, by adding the following:

\'\'Critical Life Limited Part Inspection

A. Inspection Requirements:

\(1\) This section contains the definitions for individual engine
piece-parts and the inspection procedures, which are necessary, when
these parts are removed from the engine.

\(2\) It is necessary to do the inspection procedures of the piece-parts
in Paragraph B when:

\(a\) The part is removed from the engine and disassembled to the level
specified in paragraph B and

\(b\) The part has accumulated more than 100 cycles since the last piece
part inspection, provided that the part is not damaged or related to the
cause of its removal from the engine.

\(3\) The inspections specified in this section do not replace or make
unnecessary other recommended inspections for these parts or other
parts.

B. Parts Requiring Inspection.

**Note:** Piece part is defined as any of the listed parts with all the
blades removed.

  ------------------------------------------- ------------- ---------------
  **Description**                             **Engine      
                                              manual**      

                                              **Section**   **Inspection
                                                            No.**

  Hub (Disk), 1st Stage Compressor:                         

  Hub Detail---All P/N's.                     72--33--31    --02, --03

  Hub Assembly---All P/N's.                   72--33--31    --02, --03

                                                            

  Disk, 13th Stage Compressor---All P/N's.    72--36--47    --02

                                                            

  HP Turbine, First Stage:                                  

  Rotor Assembly---All P/N's.                 72--52--02    --04

  Disk---All P/N's                            72--52--02    --03

  Disk, 2nd Stage Turbine---All P/N's.        72--53--16    --02

  Disk, 3rd Stage Turbine---All P/N's.        72--53--17    --02

  Disk, 4th Stage Turbine---All P/N's.        72--53--18    --02''
  ------------------------------------------- ------------- ---------------

\(b\) Except as provided in paragraph (c) of this AD, and
notwithstanding contrary provisions in section 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these mandatory inspections must be
performed using the TLS of the PW JT8D-200 Turbofan Engine Manual.

**Alternative Methods of Compliance**

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

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

**Ferry Flights**

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

**Continuous Airworthiness Maintenance Program**

\(e\) FAA-certificated air carriers that have an approved continuous
airworthiness maintenance program in accordance with the record keeping
requirement of Sec. 121.369(c) of the Federal Aviation Regulations (14
CFR 121.369(c)) must maintain records of the mandatory inspections that
result from revising the TLS of the PW JT8D-200 Turbofan Engine Manual,
and the air carrier\'s continuous airworthiness program. Alternatively,
certificated air carriers may establish an approved system of record
retention that provides a method for preservation and retrieval of the
maintenance

records that include the inspections resulting from this AD, and include
the policy and procedures for implementing this alternate method in the
air carrier\'s maintenance manual required by Sec. 121.369(c) of the
Federal Aviation Regulations (14 CFR 121.369(c)); however, the alternate
system must be accepted by the appropriate PMI and require the
maintenance records be maintained either indefinitely or until the work
is repeated. Records of the piece-part inspections are not required
under Sec. 121.380 (a)(2)(vi) of the Federal Aviation Regulations (14
CFR 121.380(a)(2)(vi)). All other operators must maintain the records of
mandatory inspections required by the applicable regulations governing
their operations.

**Note 3:** The requirements of this AD have been met when the engine
manual changes are made and air carriers have modified their continuous
airworthiness maintenance plans to reflect the requirements in the PW
JT8D-200 Turbofan Engine Manual.

**Effective Date**

\(f\) This amendment becomes effective on December 30, 2002.

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

Issued in Burlington, Massachusetts, on June 18, 2002.

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

\[FR Doc. 02-16535 Filed 7-2-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-03 McDonnell Douglas:** Amendment 39-12803. Docket
2002-NM-168-AD.

**Applicability:** Model MD-11 and -11F airplanes listed as Group 1 or
Group 2 airplanes in Boeing Alert Service Bulletin MD11-57A067,
including Appendices A and B, dated July 10, 2002; certificated in any
category.

**Note 1:** This AD applies to each airplane 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 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 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 and correct loose preload-indicating (PLI) washers or cracked
or corroded nuts of the lower bolts of the inboard flap outboard hinge,
which could result in separation of the inboard flap outboard hinge from
the wing structure and consequent reduced controllability of the
airplane, accomplish the following:

**Inspection**

\(a\) At the applicable time specified in paragraph (a)(1) or (a)(2) of
this AD, do a detailed inspection (including removing sealant from the
head and nut sides of both bolt assemblies) of the nuts and PLI washers
of the lower bolts of the inboard flap outboard hinge to detect
discrepancies (including loose PLI washers or cracked or corroded nuts,
as applicable), in accordance with Boeing Alert Service Bulletin
MD11-57A067, including Appendices A and B, dated July 10, 2002, except
as required by paragraphs (b) and (c) of this AD. Before further flight
thereafter, do applicable follow-on and corrective actions (including
performing a magnetic particle inspection of the bolt to detect cracking
and corrosion, replacing discrepant parts with new Inconel and/or alloy
steel bolts and nuts and new PLI washers, and applying sealant, as
applicable); and, within 600 flight cycles, replace discrepant bolts,
nuts, and washers with new parts, as applicable; in accordance with the
alert service bulletin.

\(1\) For Group 1 airplanes: Inspect within 30 days after the effective
date of this AD.

\(2\) For Group 2 airplanes: Inspect within 60 days after the effective
date of this AD.

**Note 2:** For the purposes of this AD, a detailed inspection is
defined as: \'\'An intensive visual examination of a specific structural
area, system, installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a direct
source of good lighting at intensity deemed appropriate by the
inspector. Inspection aids such as mirror, magnifying lenses, etc., may
be used. Surface cleaning and elaborate access procedures may be
required.\'\'

**Exceptions to Paragraph (a) Requirements**

\(b\) Where Boeing Alert Service Bulletin MD11-57A067, including
Appendices A and B, dated July 10, 2002, specifies that testing for
looseness of the PLI washers may be accomplished by the use of a wiggle
tool, \'\'or equivalent\'\': Either the wiggle tool must be used, or the
test must be accomplished in accordance with a method approved by the
Manager, Los Angeles Aircraft Certification Office (ACO), FAA.

\(c\) Where Boeing Alert Service Bulletin MD11-57A067, including
Appendices A and B, dated July 10, 2002, specifies to contact Boeing for
\'\'additional examination recommendations\'\': Before further flight,
these actions, if accomplished, must be performed in accordance with a
method approved by the Manager, Los Angeles ACO. For such a method to be
approved by the Manager, Los Angeles ACO, as required by this paragraph,
the Manager\'s approval letter must specifically refer to this AD.

**Reporting Requirement**

\(d\) At the applicable time specified in paragraph (d)(1) or (d)(2) of
this AD: Send a report of the results (both positive and negative) of
the inspection nuts and PLI washers of the lower bolts of the inboard
flap outboard hinge to the Manager, Los Angeles ACO, FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137, fax (562) 627-5210. The report must
include the factory serial number of the airplane; inspection results
for all four bolts; a description of any discrepancies found; the part
numbers for the bolt, nut, and PLI washers; and the total number of
landings and flight hours accumulated on the airplane. Information
collection requirements contained in this AD have been approved by the
Office of Management and Budget (OMB) under the provisions of the
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been
assigned OMB Control Number 2120-0056.

\(1\) For airplanes on which the inspection is accomplished after the
effective date of this AD: Submit the report within 10 days after
performing the inspection required by paragraph (a) of this AD.

\(2\) For airplanes on which the inspection has been accomplished prior
to the effective date of this AD: Submit the report within 10 days after
the effective date of this AD.

**Alternative Methods of Compliance**

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

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

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

**Incorporation by Reference**

\(g\) Except as required by paragraphs (b) and (c) of this AD: The
actions must be done in accordance with Boeing Alert Service Bulletin
MD11-57A067, including Appendices A and B, dated July 10, 2002. 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 Boeing Commercial Aircraft Group, Long Beach
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(h\) This amendment becomes effective on August 2, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Ronald
Atmur, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
California 90712-4137; telephone (562) 627-5224; fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Editor/Writer; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 10, 2002.

Vi Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02-18024 Filed 7-17-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-04 McDonnell Douglas:** Amendment 39-12804. Docket
2001-NM-53-AD.

**Applicability:** Model MD-11 and -11F airplanes, as listed in Boeing
Service Bulletin MD11-26-037, dated November 8, 2000; certificated in
any category.

**Note 1:** This AD applies to each airplane 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 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 (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 prevent chafing and possible damage to the wiring of the Firex bottle
discharge cartridge of the No. 2 engine, which could result in improper
distribution of the fire extinguishing agent within the No. 2 engine in
the event of a fire, accomplish the following:

**General Visual Inspection**

\(a\) Within 15 months after the effective date of this AD, do a general
visual inspection of the wiring of the Firex bottle discharge cartridge
of the No. 2 engine at station Y=2163.00 bulkhead for chafing on
adjacent structure and damaged wiring, per Boeing Service Bulletin
MD11-26-037, dated November 8, 2000.

**Note 2:** For the purposes of this AD, a general visual inspection is
defined as: \'\'A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in the inspection area.
This level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or droplight
and may require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.\'\'

**Note 3:** Where there are differences between the referenced service
bulletin and the AD, the AD prevails.

*Condition 1 (No Chafing or Damaged Wiring)*

\(1\) If no chafing or damaged wiring is detected, no further action is
required by this AD.

*Condition 2 (Chafing with No Damaged Wiring)*

\(2\) If any chafing with no damaged wiring is detected, before further
flight, reposition wires, per the service bulletin.

*Condition 3 (Chafing with Damaged Wiring)*

\(3\) If any chafing with damaged wiring is detected, before further
flight, repair damaged wires and reposition wires, per the service
bulletin.

**Alternative Methods of Compliance**

\(b\) 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, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

**Note 4:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The actions shall be done in accordance with Boeing Service
Bulletin MD11-26-037, dated November 8, 2000. 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 Boeing Commercial Aircraft Group, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data
and Service Management, Dept. C1-L5A (D800-0024). Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17526 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-05 McDonnell Douglas:** Amendment 39-12805. Docket
2001-NM-55-AD. Supersedes AD 99-26-03 C1, Amendment 39-11463.

**Applicability:** Model MD-11 airplanes, as listed in Boeing Service
Bulletin MD11-24-184, dated February 22, 2001; certificated in any
category.

**Note 1:** This AD applies to each airplane 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 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 (d)(1) 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 damage to the wire assembly terminal lugs and power feeder
cables due to the accumulated effects over time from overheating of the
power feeder cables on the No. 3 and 4 galley load control unit (GLCU),
which could result in smoke and fire in the central accessory
compartment, accomplish the following:

**Restatement of Requirements of AD 99-26-03 C1**

*Repetitive Inspections and Replacement, If Necessary*

\(a\) For airplanes listed in McDonnell Douglas Alert Service Bulletin
MD11-24A160, Revision 01, dated November 11, 1999: Within 60 days after
January 4, 2000 (the effective date of AD 99-26-03 C1, amendment
39-11463), perform a general visual inspection of the power feeder
cables, terminal strip, fuseholder, and fuses of the GLCU within the No.
3 bay electrical power center to detect damage (i.e., discoloration of
affected parts or loose attachments), in accordance with McDonnell
Douglas Alert Service Bulletin MD11-24A160, dated August 30, 1999; or
Revision 01, dated November 11, 1999.

**Note 2:** For the purposes of this AD, a general visual inspection is
defined as: \'\'A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in

the inspection area. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or droplight and may require removal or opening of access
panels or doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.\'\'

\(1\) If no damage is detected during any inspection required by this
AD, repeat the general visual inspection thereafter at intervals not to
exceed 600 flight hours.

\(2\) If any damage is detected during any inspection required by this
AD, prior to further flight, replace the power feeder cables,
fuseholder, and/or fuses, as applicable, in accordance with the service
bulletin. Repeat the general visual inspection thereafter at intervals
not to exceed 600 flight hours.

**New Actions Required By This AD**

*Repetitive Inspections and Replacement, If Necessary*

\(b\) For airplanes having serial numbers 547 and 554: Within 60 days
after the effective date of this AD, do the actions required by
paragraphs (a), (a)(1), and (a)(2) of this AD, as applicable.

*Replacement*

\(c\) Within 12 months after the effective date of this AD, replace the
electrical wiring of the galley in the electrical power center in bays
1, 2, and 3 with larger gage cable assemblies, in accordance with Boeing
Service Bulletin MD11-24-184, dated February 22, 2001. Accomplishment of
the replacement constitutes terminating action for the repetitive
inspection requirements of paragraphs (a) and (b) of this AD.

*Alternative Methods of Compliance*

(d)(1) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

\(2\) Alternative methods of compliance, approved previously in
accordance with ADs 99-26-03 and 99-26-03 C1, both having amendment
39-11463, are approved as alternative methods of compliance with this
AD.

**Special Flight Permits**

\(e\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(f\) The actions shall be done in accordance with McDonnell Douglas
Alert Service Bulletin MD11-24A160, dated August 30, 1999, or McDonnell
Douglas Alert Service Bulletin MD11-24A160, Revision 01, dated November
11, 1999; and Boeing Service Bulletin MD11-24-184, dated February 22,
2001; as applicable.

\(1\) The incorporation by reference of Boeing Service Bulletin
MD11-24-184, dated February 22, 2001, is approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

\(2\) The incorporation by reference of McDonnell Douglas Alert Service
Bulletin MD11-24A160, dated August 30, 1999; and McDonnell Douglas Alert
Service Bulletin MD11-24A160, Revision 01, dated November 11, 1999; was
approved previously by the Director of the Federal Register as of
January 4, 2000 (64 FR 71001, December 20, 1999).

\(3\) Copies may be obtained from Boeing Commercial Aircraft Group, Long
Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(g\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17527 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-06 McDonnell Douglas:** Amendment 39-12806. Docket
2001-NM-59-AD.

**Applicability:** Model MD-11 and -11F airplanes, as listed in Boeing
Service Bulletin MD11-24-197, dated May 16, 2001; certificated in any
category.

**Note 1:** This AD applies to each airplane 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 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 (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.

**Installation**

\(a\) Within 18 months after the effective date of this AD, install
protective sleeving on the right emergency wire assembly of the overhead
switch panel, per Boeing Service Bulletin MD11-24-197, dated May 16,
2001.

**Alternative Methods of Compliance**

\(b\) 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, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

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

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The installation shall be done in accordance with Boeing Service
Bulletin MD11-24-197, dated May 16, 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 Boeing Commercial Aircraft Group, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data
and Service Management, Dept. C1-L5A (D800-0024). Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17528 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-07 McDonnell Douglas:** Amendment 39-12807. Docket
2001-NM-60-AD.

**Applicability:** Model MD-11 and -11F airplanes, as listed in Boeing
Alert Service Bulletin MD11-24A036, Revision 01, dated May 21, 2001;
certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 prevent chafing and compression of electrical wiring at the upper
track mod blocks on the flight compartment floor beams in the avionics
compartment beneath the Captain\'s and First Officer\'s seats, which
could result in electrical arcing and consequent smoke and/or fire in
the cockpit, accomplish the following:

**Relocation of Mod Block Tracks**

\(a\) Within 1 year after the effective date of this AD, relocate the
mod block tracks on the flight compartment floor beams in the avionics
compartment beneath the Captain\'s and First Officer\'s seats, per
Boeing Alert Service Bulletin MD-1124A036, Revision 01, dated May 21,
2001.

**Note 2:** Accomplishment of the relocation per McDonnell Douglas
Service Bulletin MD11-24-036, dated May 8, 1992, before the effective
date of this AD, is considered acceptable for compliance with the
requirements of this AD.

**Alternative Methods of Compliance**

\(b\) 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, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The actions shall be done in accordance with Boeing Alert Service
Bulletin MD11-24A036, Revision 01, dated May 21, 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 Boeing Commercial Aircraft Group, Long Beach
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California
90712; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** *Technical Information:* Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

*Other Information:* Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17534 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-08 McDonnell Douglas:** Amendment 39-12808. Docket
2001-NM-61-AD.

**Applicability:** Model MD-11 and -11F airplanes, as listed in Boeing
Alert Service Bulletin MD11-23A046, Revision 01, dated May 21, 2001;
certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 prevent chafing of wiring in the avionics compartment, which could
result in electrical arcing and consequent smoke and/or fire in the
cockpit, accomplish the following:

\(a\) Within 1 year after the effective date of this AD, do a general
visual inspection to detect discrepancies (i.e., chafing, improper
routing or bundle support, missing tie wraps, improper clearance) of
wire bundles in the avionics compartment in the vicinity of the pedestal
extension area of the First Officer\'s seat, per the Accomplishment
Instructions of Boeing Alert Service Bulletin MD11-23A046, Revision 01,
dated May 21, 2001. If any discrepancy is detected, before further
flight, perform the applicable corrective actions (i.e., repair,
replacement of damaged wires with new wires, reroute wire bundle, and
tie wrap bundle) per the Accomplishment Instructions of the service
bulletin.

**Note 2:** For the purposes of this AD, a general visual inspection is
defined as: \'\'A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in the inspection area.
This level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or droplight
and may require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.\'\'

**Note 3:** Accomplishment of the inspections and corrective actions, if
necessary, per McDonnell Douglas Service Bulletin MD11-23-046, dated
March 17, 1995, before the effective date of this AD, is considered
acceptable for compliance with the requirements of this AD.

**Alternative Methods of Compliance**

\(b\) 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, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

**Note 4:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The actions shall be done in accordance with Boeing Alert Service
Bulletin MD11-23A046, Revision 01, dated May 21, 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 Boeing Commercial Aircraft Group, Long Beach
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17535 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-09 McDonnell Douglas:** Amendment 39-12809. Docket
2001-NM-63-AD. Supersedes AD 2000-03-15, Amendment 39-11574.

**Applicability:** Model MD-11 and MD-11F airplanes, as listed in
McDonnell Douglas Alert Service Bulletin MD11-24A150, dated March 25,
1999; and McDonnell Douglas Alert Service Bulletin MD11-24A178, Revision
01, dated December 17, 2001; certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 as indicated, unless accomplished previously.

To prevent electrical arcing caused by power feeder cable terminal lugs
grounding against terminal strip support brackets, which could result in
smoke and fire in the main cabin or avionics compartment, accomplish the
following:

**Restatement of Certain Requirements of AD 2000-03-15**

*Replacement of Terminal Strips and Supports*

\(a\) For airplanes listed in the effectivity of McDonnell Douglas Alert
Service Bulletin MD11-24A150, dated March 25, 1999, on which the
modification specified in McDonnell Douglas Service Bulletin
MD11-24-085, dated August 1, 1995, has not been accomplished: Within 1
year after March 23, 2000 (the effective date of AD 2000-03-15,
amendment 39-11574), replace the existing terminal strips and supports
above the main cabin at station Y=5-32.000 with new terminal strips and
supports in accordance with McDonnell Douglas Alert Service Bulletin
MD11-24A150, dated March 25, 1999.

**New Actions Required by This AD**

*Replacement, Inspection, and Corrective Action If Necessary*

\(b\) For airplanes listed in the effectivity of McDonnell Douglas Alert
Service Bulletin MD11-24A178, Revision 01, dated December 17, 2001:
Within 18 months after the effective date of this AD, do the actions
specified in paragraphs (b)(1) and (b)(2) of this AD per the service
bulletin.

\(1\) Replace the applicable terminal strips in the avionics compartment
with new terminal strips (including inspecting wires for damage,
repairing any damaged wire, and removing the nameplate); and

\(2\) Perform a general visual inspection to detect arcing damage of the
surrounding structure of the terminal strips and electrical cables in
the avionics compartment. If any damage is detected, before further
flight, repair or replace any damaged component with a new component,
per the service bulletin; except if the type of structural material of
the surrounding structure that has been affected is not covered in the
Structural Repair Manual, repair per a method approved by the Manager,
Los Angeles Aircraft Certification Office (ACO), FAA.

**Note 2:** For the purposes of this AD, a general visual inspection is
defined as \'\'A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight, or
drop-light, and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain proximity
to the area being checked.\'\'

**Note 3:** Accomplishment of the replacement, inspection, and
corrective action, before the effective date of this AD, per McDonnell
Douglas Alert Service Bulletin MD11-24A178, dated May 14, 2001, is
considered acceptable for compliance with the applicable actions
specified in this amendment.

**Alternative Methods of Compliance**

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

Note 4: Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(d\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(e\) Except as provided by paragraph (b)(2) of this AD, the actions
shall be done in accordance with McDonnell Douglas Alert Service
Bulletin MD11-24A150, dated March 25, 1999; and McDonnell Douglas Alert
Service Bulletin MD11-24A178, Revision 01, dated December 17, 2001; as
applicable.

\(1\) The incorporation by reference of McDonnell Douglas Alert Service
Bulletin MD11-24A178, Revision 01, dated December 17, 2001, is approved
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.

\(2\) The incorporation by reference of McDonnell Douglas Alert Service
Bulletin MD11-24A150, dated March 25, 1999, was approved previously by
the Director of the Federal Register as of March 23, 2000 (65 FR 8025,
February 17, 2000).

\(3\) Copies may be obtained from Boeing Commercial Aircraft Group, Long
Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(f\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17536 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-10 McDonnell Douglas:** Amendment 39-12810. Docket
2001-NM-64-AD.

**Applicability:** Model MD-11 and -11F airplanes, certificated in any
category; equipped with United Technologies Pratt & Whitney Model PW4460
or PW4462 engines, engine buildup units having neutral quick engine
change, cum units 4 through 240 inclusive and serial numbers 5166001
through 5213003 inclusive.

**Note 1:** This AD applies to each airplane 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 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 (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 as indicated, unless accomplished previously.

To prevent arcing of the integrated drive generator (IDG) wire harness,
which could result in smoke and/or fire in the area of the forward
engine mount bolt retainer and/or fire detector responder, accomplish
the following:

**Replacement and Modification**

\(a\) Within 1 year after the effective date of this AD, replace the
wire harness support bracket of the IDG of the forward engine mounts
with a new support bracket, and modify the angle of the bracket near the
oil filter (i.e., cut and grind flanges, deburr edges, fusion weld
flanges, and reidentify bracket), per Boeing Alert Service Bulletin
MD11-71A086, Revision 01, dated May 21, 2001.

**Note 2:** Boeing Alert Service Bulletin MD11-71A086 references United
Technologies Pratt & Whitney Service Bulletin PW4MD11 71-107, dated May
15, 1996, as an additional source of service information for
accomplishing the proposed replacement and modification.

**Spares**

\(b\) As of the effective date of this AD, no United Technologies Pratt
& Whitney Model PW4460 or PW4462 engines, engine buildup units having
neutral quick engine change, cum units 4 through 240 inclusive and
serial numbers 5166001 through 5213003 inclusive, shall be installed on
any airplane unless the requirements of paragraph (a) of this AD have
been done.

**Alternative Methods of Compliance**

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

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permit**

\(d\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(e\) The replacement and modification shall be done in accordance with
Boeing Alert Service Bulletin MD11-71A086, Revision 01, dated May 21,
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 Boeing Commercial Aircraft Group, Long
Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(f\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712; telephone (562) 627-5350; fax
(562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17529 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-11 McDonnell Douglas:** Amendment 39-12811. Docket
2001-NM-65-AD. Supersedes AD 2000-24-13, Amendment 39-12020.

**Applicability:** Model MD-11 and -11F airplanes, as listed in
McDonnell Douglas Alert Service Bulletin MD11-24A138, Revision 01, dated
June 5, 2001; certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 as indicated, unless accomplished previously.

To prevent arcing and heat damage to the attachment points of the main
external and galley power receptacle ground wire, insulation blankets
outboard and aft of the receptacle area, and adjacent power cables,
which could result in smoke and fire in the forward cargo compartment,
accomplish the following:

**Replacement and Rerouting**

\(a\) Within 12 months after January 8, 2001 (the effective date of AD
2000-24-13, amendment 39-12020), accomplish the actions specified in
paragraph (a)(1) or (a)(2) of this AD, as applicable, in accordance with
McDonnell Douglas Alert Service Bulletin MD11-24A138, dated April 3,
2000, or Revision 01, dated June 5, 2001. As of the effective date of
this AD, only Revision 01 of the service bulletin shall be used.

\(1\) For Group 1 airplanes listed in the original version of the
service bulletin, excluding fuselage number 0456: Replace the ground
support brackets with new brackets and reroute the ground cables of the
galley external power and main external power.

\(2\) For Group 2 airplanes listed in the original version of the
service bulletin and fuselage number 0456: Replace the ground support
bracket and reroute the ground cables of the main external power.

**Inspection and Corrective Actions, If Necessary**

\(b\) Within 12 months after the effective date of this AD, accomplish
the actions specified in paragraph (b)(1) or (b)(2) of this AD, as
applicable, in accordance with McDonnell Douglas Alert Service Bulletin
MD11-24A138, Revision 01, dated June 5, 2001.

\(1\) For Group 3 airplanes listed in Revision 01 of the service
bulletin: Do a general visual inspection of the ground cables of the
main external power and galley external power for excessive length. If
any cable length is excessive, before further flight, do applicable
corrective actions (e.g., cut cable assembly to correct length and
install a terminal on the cut end of the cable) per Condition 2 of
Figure 3 of the service bulletin.

\(2\) For Group 4 airplanes listed in Revision 01 of the service
bulletin: Do a general visual inspection of the ground cables of the
main external power for excessive length. If any cable length is
excessive, before further flight, do applicable corrective actions
(e.g., cut cable assembly to correct length and install a terminal on
the cut end of the cable) per Condition 2 of Figure 4 of the service
bulletin.

**Note 2:** For the purposes of this AD, a general visual inspection is
defined as: \'\'A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in the inspection area.
This level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or droplight
and may require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.\'\'

**Alternative Methods of Compliance**

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

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(d\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(e\) The actions shall be done in accordance with McDonnell Douglas
Alert Service Bulletin MD11-24A138, dated April 3, 2000, or McDonnell
Douglas Alert Service Bulletin MD11-24A138, Revision 01, dated June 5,
2001; as applicable.

\(1\) This incorporation by reference of McDonnell Douglas Alert Service
Bulletin MD11-24A138, Revision 01, dated June 5, 2001, is approved by
the Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51.

\(2\) The incorporation by reference of McDonnell Douglas Alert Service
Bulletin MD11-24A138, dated April 3, 2000, was approved previously by
the Director of the Federal Register as of January 8, 2001 (65 FR 75616,
December 4, 2000).

\(3\) Copies may be obtained from Boeing Commercial Aircraft Group, Long
Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(f\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17530 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-12 McDonnell Douglas:** Amendment 39-12812. Docket
2001-NM-157-AD.

**Applicability:** Model MD-11 and -11F airplanes, as listed in Boeing
Alert Service Bulletin MD11-28A058, Revision 01, dated March 29, 2001;
certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 prevent chafing of the wiring in a cutout area in the wing fuel
control panel due to improperly routed wiring, which could result in
electrical arcing in an abnormal fuel vapor zone and consequent possible
ignition of the fuel vapor, accomplish the following:

**Inspection and Corrective Action, If Necessary**

\(a\) Within 6 months after the effective date of this AD, do a general
visual inspection of the wiring in the fuel control panel of the wings
for chafing damage and for proper routing of the wiring, per Boeing
Alert Service Bulletin MD11-28A058, Revision 01, dated March 29, 2001.

**Note 2:** For the purposes of this AD, a general visual inspection is
defined as: \'\'A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in the inspection area.
This level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or droplight
and may require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.\'\'

\(1\) Condition 1. If no chafing damage is found and if the wiring is
NOT routed into the cutout area of the fuel control panel, no further
work is required by this AD.

\(2\) Condition 2. If no chafing damage is found and if the wiring is
routed into the cutout area of the fuel control panel, before further
flight, revise the wire routing out of the cutout area in the fuel
control panel, per the service bulletin.

\(3\) Condition 3. If any chafing damage is found and if the wiring is
routed into the cutout area of the fuel control panel, before further
flight, replace any damaged wire with a new wire, and revise the wire
routing out of the cutout area in the fuel control panel, per the
service bulletin.

**Note 3:** Accomplishment of the actions specified in McDonnell Douglas
service Bulletin MD11-28-058, dated January 3, 1995, before the
effective date of this AD, is considered acceptable for compliance with
the requirements of this AD.

**Alternative Methods of Compliance**

\(b\) 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, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

**Note 4:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The actions shall be done in accordance with Boeing Alert Service
Bulletin MD11-28A058, Revision 01, dated March 29, 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 Boeing Commercial Aircraft Group, Long Beach
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17531 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-13 McDonnell Douglas:** Amendment 39-12813. Docket
2001-NM-158-AD.

**Applicability:** Model MD-11 and -11F airplanes, as listed in Boeing
Alert Service Bulletin MD11-52A035, Revision 02, dated March 12, 2001;
certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 prevent failure of the wire assemblies and damage of a ballast of a
light fixture, and consequent smoke and/or fire in the forward cargo
compartment, accomplish the following:

**Installation of Clipnut and Bracket and Revision of Routing of
Wiring**

\(a\) Within 1 year after the effective date of this AD, install a
clipnut and bracket and revise the routing of the wire assembly of the
forward lower cargo door, per Boeing Alert Service Bulletin MD11-52A035,
Revision 02, dated March 12, 2001.

**Note 2:** Accomplishment of the actions specified in McDonnell Douglas
Service Bulletin MD11-52-035, Revision 01, dated March 9, 1998, before
the effective date of this AD, is considered acceptable for compliance
with the requirements of this AD.

**Alternative Methods of Compliance**

\(b\) 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, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The actions shall be done in accordance with Boeing Alert Service
Bulletin MD11-52A035, Revision 02, dated March 12, 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 Boeing Commercial Aircraft Group, Long Beach
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17532 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-14 McDonnell Douglas:** Amendment 39-12814. Docket
2001-NM-159-AD.

**Applicability:** Model MD-11 and -11F airplanes equipped with General
Electric tail engine buildup units (EBU), as listed in Boeing Alert
Service Bulletin MD11-24A095, Revision 01, dated March 16, 2001;
certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 prevent chafing and arcing of the wire harness of the integrated
drive generator (IDG) due to inadequate support, which could result in
smoke and/or fire in the area of the forward engine mount, accomplish
the following:

**Installation of New Support Bracket**

\(a\) Within 1 year after the effective date of this AD, install a new
support bracket with a clamp and screw to support the wire harness of
the IDG, per Boeing Alert Service Bulletin MD11-24A095, Revision 01,
dated March 16, 2001.

**Note 2:** Accomplishment of the installation per McDonnell Douglas
Service Bulletin MD11-24-095, dated January 29, 1996, before the
effective date of this AD, is considered acceptable for compliance with
the requirements of paragraph (a) of this AD.

**Alternative Methods of Compliance**

\(b\) 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, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The installation shall be done in accordance with Boeing Alert
Service Bulletin MD11-24A095, Revision 01, dated March 16, 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 Boeing Commercial Aircraft Group, Long Beach
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on August 23, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5350;
fax (562) 627-5210.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17533 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**MCDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-15 McDonnell Douglas:** Amendment 39-12815. Docket
2002-NM-33-AD. Supersedes AD 2000-14-18, Amendment 39-11829.

**Applicability:** Model MD-11 and -11F airplanes, as listed in
McDonnell Douglas Alert Service Bulletin MD11-25A227, Revision 01, dated
October 31, 2001; certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 ensure that the powered roller pans are positioned properly,
accomplish the following:

\(a\) Within 18 months after the effective date of this AD, accomplish
the actions specified in paragraphs (a)(1), (a)(2), and (a)(3) of this
AD per McDonnell Douglas Alert Service Bulletin MD11-25A227, Revision
01, dated October 31, 2001.

**Inspection**

\(1\) Perform a general visual inspection of the powered drive unit
power wires within three feet of each affected powered drive unit
termination for mechanical damage. If any damaged wire is detected,
before further flight, repair the damaged wire.

**Note 2:** For the purposes of this AD, a general visual inspection is
defined as: \"A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in the inspection area.
This level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or droplight
and may require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.\'\'

**Revise Wire Harnesses, Splice Wire, and Route and Install Parts**

\(2\) Revise the wire harnesses, splice any additional length wire, and
route and install parts.

**Replacement**

\(3\) Replace the floor panels with new and retained floor panels.

**Alternative Methods of Compliance**

\(b\) 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, Los Angeles Aircraft Certification Office
(ACO), FAA. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles ACO.

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The actions shall be done in accordance with McDonnell Douglas
Alert Service Bulletin MD11-25A227, Revision 01, dated October 31, 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 Boeing Commercial Aircraft Group, Long Beach
Division, 3855 Lakewood Boulevard, Long Beach, California 90846,
Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies
may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California; or
at the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on August 5, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Brett
Portwood, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5350; fax (562) 627-5210.

Other Information: Sandi Carli, Airworthiness Directive Technical
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <sandi.carli@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 2, 2002.

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17525 Filed 7-18-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**ROCKWELL COLLINS, INC.**

**AIRWORTHINESS DIRECTIVE**

**APPLIANCE**

**LARGE AIRCRAFT**

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

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

\(1\) Affected ADC\'s:

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

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

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

  ADC-85/ADC-85A              Astra AIA.

                              Chinese Y7 and Y8.

                              Czech LET-610.

                              DC-8.

                              Falcon 20F.

                              Piaggio P-180.

                              Raytheon B200, B300, C90A and 1900D.

  ADC-850D                    Lear 60.

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

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

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

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

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

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

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

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

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

**Note 2:** This AD applies to each airplane identified in paragraph (a)
of this AD, regardless of whether it has been modified, altered, or
repaired in the area subject to the requirements of this AD. For
airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD; and,
if you have not eliminated the unsafe condition, specific actions you
propose to address it.

\(f\) *Where can I get information about any already-approved
alternative methods of compliance?* Contact Roger A. Souter, FAA,
Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room
100, Wichita, Kansas 67209; telephone: (316) 946-4134; facsimile: (316)
946-4407, E-mail: <Roger.Souter@faa.gov>.

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

\(h\) *Are any service bulletins incorporated into this AD by
reference?* Actions required by this AD must be done in accordance with
Rockwell Collins Service Bulletin No. 62, Revision No. 2,
ADC-85/85A/850C/850D/850E/850F-34-62, dated March 7, 2000, or Rockwell
Collins Service Bulletin No. 62, ADC-85/85A/850C/850F-34-62, dated
October 25, 1999. The Director of the Federal Register approved this
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You
may get copies from Rockwell Collins, Business and Regional Systems, 400
Collins Road Northeast, Cedar Rapids, Iowa 52498. You may view copies at
the FAA, Central Region, Office of the Regional Counsel, 901 Locust,
Room 506, Kansas City, Missouri, or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

\(i\) *When does this amendment become effective ?* This amendment
becomes effective on August 23, 2002.

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

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

Dorenda D. Baker,

Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.

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

BILLING CODE 4910-13-P

**BW 2002-15**

**BOEING**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**EDITORIAL CORRECTION** *published in Federal Register July 22, 2002,
\[Volume 67, Number 140); Page 47891;
www.access.gpo.gov/su_docs/aces/aces140.html\]*

**2002-14-20 Boeing:** Amendment 39-12820. Docket 2002-NM-127-AD.

**Applicability:** Model 737-600, -700, -800, and -900 series airplanes;
as listed in Boeing Alert Service Bulletin 737-24A1150, dated April 11,
2002; certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 prevent ice from blocking the pitot tube that provides airspeed data
to the flightcrew, which could lead to the flightcrew receiving
incorrect airspeed data, and result in loss of control of the airplane
if the flightcrew fails to recognize that the data are incorrect,
accomplish the following:

**Measurement of Voltage and Corrective Actions**

\(a\) Within 60 days after the effective date of this AD, measure the
electrical voltage at the circuit breaker for the captain\'s pitot
heater to determine if the pitot heater is connected to the correct
power supply bus, per Boeing Alert Service Bulletin 737-24A1150, dated
April 11, 2002.

\(1\) If the measurement is 100 to 122 volts alternating current (AC):
No further action is required by this AD.

\(2\) If the measurement is not 100 to 122 volts AC: Before further
flight, perform all actions associated with connecting the subject
circuit breaker wire to the 115-volt AC standby power supply bus
(including performing a test to ensure that the pitot heater system
operates correctly, repeating the measurement of the electrical voltage
at the circuit breaker for the captain\'s pitot heater, and
troubleshooting and correcting the wire connections until the test and
measurement are successful), per the service bulletin.

**Alternative Methods of Compliance**

\(b\) 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, Seattle Aircraft Certification Office (ACO),
FAA. Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send it
to the Manager, Seattle ACO.

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

**Special Flight Permits**

\(c\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(d\) The actions shall be done in accordance with Boeing Alert Service
Bulletin 737-24A1150, dated April 11, 2002. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
the Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on July 31, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Binh Tran,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington
98055-4056; telephone (425) 227-2890; fax (425) 227-1181.

Other Information: Judy Golder, Airworthiness Directive Technical
Editor/Writer; telephone (425) 687-4241, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: <judy.golder@faa.gov>. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.

Issued in Renton, Washington, on July 8, 2002.

Vi Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02-17548 Filed 7-15-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**BOEING**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-21 Boeing:** Amendment 39-12821. Docket 2000-NM-367-AD.
Supersedes AD 99-03-08, Amendment 39-11022.

**Applicability:** Model 737-600, -700, and -800 series airplanes,
listed in Group I or II of Boeing Alert Service Bulletin 737-73A1011,
Revision 2, dated July 13, 2000; certificated in any category.

**Note 1:** This AD applies to Model 737-700 series airplanes in an
increased-gross-weight configuration, as listed in the service bulletin
referred to in the applicability statement of this AD.

**Note 2:** This AD applies to each airplane 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 airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (f)(1) 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 major fuel leakage due to excessive wear of the
quick-disconnect coupling on the fuel hose, fire in the engine nacelle,
and consequent loss of thrust from the affected engine, which could
result in reduced controllability of the airplane, accomplish the
following:

**Restatement of Requirements of AD 99-03-08**

*Repetitive Inspections and Corrective Actions*

\(a\) For airplanes listed in Group I of Boeing Alert Service Bulletin
737-73A1011, Revision 2, dated July 13, 2000: Within 7 days after
February 19, 1999 (the effective date of AD 99-03-08, amendment
39-11022), perform a general visual inspection to detect discrepancies
(i.e., fuel leakage, wear of the lock teeth, or missing lock pins on the
coupling nut) of the quick-disconnect coupling on the fuel hose located
at the fan case firewall, in accordance with Boeing Alert Service
Bulletin 737-73A1011, dated November 25, 1998; or Revision 2, dated July
13, 2000.

\(1\) If no discrepancy is detected, repeat the inspection thereafter at
intervals not to exceed 500 flight hours, until the installation
required by paragraph (b) of this AD is accomplished.

\(2\) If any discrepancy is detected, prior to further flight, perform
follow-on corrective actions, as applicable, in accordance with TABLE 1.
of the Accomplishment Instructions of the alert service bulletin, and
repeat the inspection thereafter at the time specified in TABLE 1. of
the Accomplishment Instructions of the alert service bulletin.

*Installation of Clamp Shell and Repetitive Inspections*

\(b\) For airplanes listed in Group I of Boeing Alert Service Bulletin
737-73A1011, Revision 2, dated July 13, 2000: Within 30 days after
February 19, 1999, install an Aeroquip Clamp Shell, having part number
(P/N) AE20074-165, on the quick-disconnect coupling on the fuel hose,
which is located at the fan case firewall, in accordance with Boeing
Alert Service Bulletin 737-73A1011, dated November 25, 1998; or Revision
2, dated July 13, 2000. Accomplishment of such installation terminates
the repetitive inspection requirements of paragraphs (a)(1) and (a)(2)
of this AD.

**New Requirements of This AD**

**Note 3:** For the purposes of this AD, a general visual inspection is
defined as: \'\'A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in the inspection area.
This level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or droplight
and may require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.\'\'

**Note 4:** Accomplishment of the requirements of paragraphs (a), (b),
and (c) of this AD according to Boeing Alert Service Bulletin
737-73A1011, Revision 1, dated April 15, 1999, is acceptable for
compliance with those paragraphs.

**Repetitive Inspections**

\(c\) For airplanes listed in Groups I and II of Boeing Alert Service
Bulletin 737-73A1011, Revision 2, dated July 13, 2000: Within 1,000
flight hours after installation of the clamp shell either per paragraph
(b) of this AD (for Group I airplanes) or during production (for Group
II airplanes), perform the inspection specified in paragraph (a) of this
AD.

**Note 5:** The repetitive inspections required by paragraph (c) of this
AD were previously required by paragraph (b) of AD 99-03-08.

\(1\) If no discrepancy is detected, repeat the inspection thereafter at
intervals not to exceed 1,000 flight hours.

\(2\) If any discrepancy is detected, prior to further flight, perform
follow-on corrective actions, as applicable, in accordance with Figures
1 and 3 of the Accomplishment Instructions of the alert service
bulletin, as applicable, and repeat the inspection thereafter at the
time specified in TABLE 1. of the Accomplishment Instructions of the
alert service bulletin.

**Replacement of Existing Parts**

\(d\) For airplanes listed in Groups I and II of Boeing Alert Service
Bulletin 737-73A1011, Revision 2, dated July 13, 2000: Within 3 years
after the effective date of this AD, remove the clamp shell installed
per paragraph (b) of this AD (for Group I airplanes) or during
production (for Group II airplanes), and replace the existing
quick-disconnect fuel hose, coupling, and strut fitting with new,
fixed-B-nut-type parts, in accordance with Boeing Alert Service Bulletin
737-73A1011, Revision 2, dated July 13, 2000. Such replacement
terminates the repetitive inspections required by paragraphs (a)(1),
(a)(2), and (c) of this AD, as applicable.

**Spares**

\(e\) After the effective date of this AD, no one may install a
quick-disconnect fuel supply hose, coupling, or strut fitting with a
part number listed in the \'\'Existing Part Number\'\' column of the
table under paragraph 2.E. of Boeing Alert Service Bulletin 737-73A1011,
Revision 2, dated July 13, 2000, on any airplane.

**Alternative Methods of Compliance**

(f)(1) 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, Seattle Aircraft Certification Office (ACO),
FAA. Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send it
to the Manager, Seattle ACO.

\(2\) Alternative methods of compliance, approved previously in
accordance with AD 99-03-08, amendment 39-11022, are approved as
alternative methods of compliance with paragraphs (a), (b), and (c) of
this AD.

**Note 6:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
Seattle ACO.

**Special Flight Permits**

\(g\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(h\) The actions shall be done in accordance with Boeing Alert Service
Bulletin 737-73A1011, dated November 25, 1998; or Boeing Alert Service
Bulletin 737-73A1011, Revision 2, dated July 13, 2000.

\(1\) The incorporation by reference of Boeing Alert Service Bulletin
737-73A1011, Revision 2, dated July 13, 2000, is approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.

\(2\) The incorporation by reference of Boeing Alert Service Bulletin
737-73A1011, dated November 25, 1998, was approved previously by the
Director of the Federal Register as of February 19, 1999 (64 FR 5590,
February 4, 1999).

\(3\) Copies may be obtained from Boeing Commercial Airplane Group, P.O.
Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.

**Effective Date**

\(i\) This amendment becomes effective on August 21, 2002.

**FOR FURTHER INFORMATION CONTACT:** Douglas Pegors, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1446; fax (425) 227-1181.

Issued in Renton, Washington, on July 8, 2002.

Vi Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02-17550 Filed 7-16-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER)**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-23 Empresa Brasileira de Aeronautica S.A. (EMBRAER):**
Amendment 39-12823. Docket 2002-NM-129-AD.

**Applicability:** Model EMB-135 and -145 series airplanes, certificated
in any category; equipped with horizontal stabilizer actuator (HSA)
assemblies having part numbers and serial numbers as listed in EMBRAER
Service Bulletin 145-27-0088, dated February 1, 2002.

**Note 1:** This AD applies to each airplane 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 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 (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 as indicated, unless accomplished previously.

To prevent a loose or disengaged clutch nut on the HSA clutch assembly,
which could result in loss of pitch trim and consequent reduced
controllability of the airplane, accomplish the following:

**Detailed Inspection and Follow-On Actions**

\(a\) Within 30 days after the effective date of this AD, perform a
one-time detailed inspection of the HSA clutch assembly to verify that
at least one locking tab on the key washer is bent into the locking
groove of the clutch nut, per EMBRAER Service Bulletin 145-27-0088,
dated February 1, 2002.

**Note 2:** For the purposes of this AD, a detailed inspection is
defined as: \'\'An intensive visual examination of a specific structural
area, system, installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a direct
source of good lighting at intensity deemed appropriate by the
inspector. Inspection aids such as mirror, magnifying lenses, etc., may
be used. Surface cleaning and elaborate access procedures may be
required.\'\'

**Note 3:** EMBRAER Service Bulletin 145-27-0088 refers to Parker
Service Bulletin 362200-27-231, dated December 21, 2001, as the
appropriate source of service information for accomplishment of the
inspection described in paragraph (a) of this AD. A copy of the Parker
service bulletin is contained within the EMBRAER service bulletin.

\(1\) If at least one locking tab is bent into the locking groove of the
clutch nut: Before further flight, perform all applicable follow-on
actions per the service bulletin. The follow-on actions include a
detailed inspection for damage (e.g., nicks, tears, scarring) of the
O-ring at the base of the HSA motor, replacement of the O-ring with a
new O-ring if any damage is found, and a detailed inspection for damage
(e.g., nicks, tears, scarring) of the sealing surface. If any damage is
found on the sealing surface, before further flight, replace the HSA
assembly with a serviceable assembly, per the service bulletin.

\(2\) If no locking tab is bent into the locking groove of the clutch
nut: Before further flight, replace the HSA assembly with a serviceable
HSA assembly, per the service bulletin.

**Spares**

\(b\) As of the effective date of this AD, no person may install on any
airplane an HSA assembly with a part number and serial number included
in the applicability statement of this AD, unless the HSA assembly has
been inspected according to paragraph (a) of this AD and found to have
at least one locking tab bent into the locking groove of the clutch nut.

**Alternative Methods of Compliance**

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

**Note 4:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
Atlanta ACO.

**Special Flight Permits**

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

**Incorporation by Reference**

\(e\) The actions shall be done in accordance with EMBRAER Service
Bulletin 145-27-0088, dated February 1, 2002. 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box
343--CEP 12.225, Sao Jose dos Campos--SP, Brazil. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; at the FAA, Atlanta Aircraft Certification
Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta,
Georgia; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.

**Note 5:** The subject of this AD is addressed in Brazilian
airworthiness directive 2002-04-01, dated April 24, 2002.

**Effective Date**

\(f\) This amendment becomes effective on August 2, 2002.

**FOR FURTHER INFORMATION CONTACT:** Robert Capezzuto, Aerospace
Engineer, Systems and Flight Test Branch, ACE-116A, FAA, Atlanta
Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard,
suite 450, Atlanta, Georgia 30349; telephone (770) 703-6071; fax (770)
703-6097.

Issued in Renton, Washington, on July 11, 2002.

Lirio Liu-Nelson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-18026 Filed 7-17-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**CESSNA AIRCRAFT COMPANY**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-24 Cessna Aircraft Company:** Amendment 39-12824. Docket
2000-NM-388-AD.

**Applicability:** Model 650 airplanes, serial numbers -0001 through
-0241 inclusive, and serial numbers -7001 through -7112 inclusive;
certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 (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 as indicated, unless accomplished previously.

To prevent inadvertent disengagement of the locking mechanism of the
side brace mechanism assembly of the left or right main landing gear
(MLG), which could lead to collapse of the respective MLG, and result in
gear-up landing and possible injury to passengers and crew; accomplish
the following:

**One-Time Inspection**

\(a\) Within 6 months after the effective date of this AD, do a one-time
inspection of the side brace mechanism assemblies of the left and right
MLGs to detect any incorrect part number (P/N) found installed, as
specified in Cessna Service Bulletin SB650-32-47, including Cessna
Service Bulletin Supplemental Data SB650-32-47, both dated August 14,
2000.

\(1\) If the correct part number is found installed on the left side
brace mechanism assembly, P/N 6217076-201, and on the right side brace
mechanism assembly, P/N 6217076-202, no further action is required by
paragraph (a) of this AD.

**Corrective Action**

\(2\) If incorrect P/N 6217076-2, 6217076-4, or 6217076-9 is found
installed on either the left or right side brace mechanism assembly:
Prior to further flight, replace any incorrect left side brace mechanism
assembly with a new, improved assembly, P/N 6217076-201; and replace any
incorrect right side brace mechanism assembly with a new, improved
assembly, P/N 6217076-202; per Cessna Service Bulletin SB650-32-47,
including Cessna Service Bulletin Supplemental Data SB650-32-47, both
dated August 14, 2000. After the replacement action, no further action
is required by this AD.

**Spares**

\(b\) As of the effective date of this AD, no person shall install a
left or right MLG side brace mechanism assembly, P/N 6217076-2,
6217076-4, or 6217076-9, on any airplane.

**Alternative Methods of Compliance**

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

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

**Special Flight Permits**

\(d\) Special flight permits may be issued in accordance with sections
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 accomplished.

**Incorporation by Reference**

\(e\) The actions shall be done in accordance with Cessna Service
Bulletin SB650-32-47, including Cessna Service Bulletin Supplemental
Data SB650-32-47, both dated August 14, 2000. 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 Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277.
Copies may be inspected at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft
Certification Office, 1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas; or at the Office of the Federal Register, 800
North Capitol Street, NW., Suite 700, Washington, DC.

**Effective Date**

\(f\) This amendment becomes effective on August 26, 2002.

**FOR FURTHER INFORMATION CONTACT:** Robert P. Busto, Aerospace
Engineer, Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft
Certification Office, 1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209; telephone (316) 946-4157; fax (316)
946-4407.

Issued in Renton, Washington, on July 11, 2002.

Lorio Liu-Nelson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-18199 Filed 7-19-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-15**

**EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER)**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-25 Empresa Brasileira De Aeronautica S.A. (Embraer):**
amendment 39-128.25 Docket 2002-NM-131-AD. Supersedes AD 2002-08-18,
Amendment 39-12730.

**Applicability:** Model EMB-135 and -145 series airplanes; certificated
in any category; equipped with horizontal stabilizer actuators as listed
in Embraer Service Bulletin 145-27-0082, Change No. 01, dated December
13, 2001.

**Note 1:** This AD applies to each airplane 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 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 (d)(1) 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 loss of pitch trim command during the takeoff and climb phase
of flight due to improper set point of the actuator clutches of the
horizontal stabilizer, which could result in high pitch control forces
and consequent reduced controllability of the airplane, accomplish the
following:

**Requirements of AD 2002-08-18, Amendment 39-12739**

*Repetitive Inspectors (Tests)/Replacement*

\(a\) For airplanes subject to the requirements of AD 2002-08-18, within
800 flight hours after May 16, 2002 (the effective date of AD
2002-08-18): Do an inspection (test) of the actuator clutches of both
the primary and backup pitch trim systems of the horizontal stabilizer
for proper pitch trim indications per EMBRAER Service Bulletin
145-27-0082, dated September 18, 2001, or Change No. 01, dated December
13, 2001. Repeat the test after that every 2,000 flight hours.

\(1\) If either test indicates that the clutch is slipping (no PIT TRIM
1 INOP or PIT TRIM 2 INOP message appears, and the measured voltage
during trim attempts is greater than 1 volt), before further flight,
replace the applicable actuator with an improved actuator and before
further flight, repeat the test.

\(2\) If both tests indicate that the clutch is acceptable (PIT TRIM 1
INOP or PIT TRIM 2 INOP message appears), repeat the test at the time
specified in paragraph (a) of this AD.

**New Requirements of This AD**

\(b\) For airplanes other than those identified in paragraph (a) of this
AD, within 800 flight hours after the effective date of this AD: Do an
inspection (test) of the actuator clutches of both the primary and
backup pitch trim systems of the horizontal stabilizer for proper pitch
trim indications per EMBRAER Service Bulletin 145-27-0082, dated
September 18, 2001, or Change No. 01, dated December 13, 2001. Repeat
the test their that every 2,000 flight hours.

\(1\) If either test indicates that the clutch is slipping (no PIT TRIM
1 INOP or PIT TRIM 2 INOP message appears, and the measured voltage
during trim attempts is greater than 1 volt), before further flight,
replace the applicable actuator with an improved actuator per the
service bulletin, and before further flight, repeat the test.

\(2\) If both tests indicate that the clutch is acceptable (PIT TRIM 1
INOP or PIT TRIM 2 INOP message appears), repeat the test at the time
specified in paragraph (a) of this AD.

**Spares**

\(c\) As of the effective date of this AD, no person shall install an
actuator having part number 362200-1007, -1009, -1011, or -1013 on any
airplane, unless the actuator clutch is inspected as required by
paragraph (a) of this AD.

**Alternative Methods of Compliance**

(d)(1) 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, Atlanta Aircraft Certification Office (ACO),
FAA. Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send it
to the Manager, Atlanta ACO.

\(2\) Alternative methods of compliance, approved previously per AD
2002-08-18, amendment 39-12730, are approved as alternative methods of
compliance with this AD.

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

**Special Flight Permits**

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

**Incorporation by Reference**

\(f\) Except as provided by paragraph (a)(1) of this AD, the actions
shall be done in accordance with EMBRAER Service Bulletin 145-27-0082,
dated September 18, 2001; or EMBRAER Service Bulletin 145-27-0082,
Change No. 01, dated December 13, 2001.

\(1\) The incorporation by reference of EMBRAER Service Bulletin
145-27-0082, Change No. 01, dated December 13, 2001, is approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.

\(2\) The incorporation by reference of EMBRAER Service Bulletin
145-27-0082, dated September 18, 2001, was approved previously by the
Director of the Federal Register as of May 16, 2002 (67 FR 21567, May 1,
2002.)

\(3\) Copies may be obtained from Empresa Brasileira de Aeronautics S.A.
(EMBRAER), P.O. Box 343-CEP 12.225, San Jose dos Campos--SP, Brazil.
Copies may be inspected at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at the FAA, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite
450, Atlanta, Georgia; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.

**Note 3:** The subject of this AD is addressed in Brazilian
airworthiness directive 2001-10-02R2, dated May 6, 2002.

**Effective Date**

\(g\) This amendment becomes effective on August 8, 2002.

**FOR FURTHER INFORMATION CONTACT:** Robert Capezzuto, Aerospace
Engineer, Systems and Flight Test Branch, ACE-116A, FAA, Atlanta
Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard,
suite 450, Atlanta, Georgia 30349; telephone (770) 703-6071; fax (770)
703-6097.

Issued in Renton, Washington, on July 11, 2002.

Michael J. Kaszycki,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-18028 Filed 7-23-02; 8:45 am\]

BILLING CODE 4910-13-M

**BW 2002-15**

**FOKKER SERVICES B.V.**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002--14--27 Fokker Services B.V.:** Amendment 39--12827. Docket
98--NM--224--AD. Supersedes AD 94--25--03, Amendment 39--9087.

**Applicability:** All Model F.28 Mark 0070, 0100, 1000, 2000, 3000, and
4000 series airplanes; certificated in any category.

**Note 1:** This AD applies to each airplane 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 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 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 takeoff with snow, ice, or frost on the critical surfaces of
the airplane, which could result in reduced controllability of the
airplane; accomplish the following:

**Restatement of Requirements of AD 94--25--03, Amendment 39--9087**

\(a\) Within 10 days after December 21, 1994 (the effective date of AD
94--25--03, amendment 39--9087), incorporate the following into the
Limitations Section of the FAA-approved Airplane Flight Manual (AFM)
(this may be accomplished by inserting a copy of this AD in the AFM):

"Wing De-Icing/Anti-Icing Prior To Takeoff

Caution

The Model F.28 series airplane has a wing design with no leading edge
high lift devices, such as slats. Wings without leading edge high lift
devices are particularly susceptible to loss of lift due to wing icing.
Minute amounts of ice or other contamination (equivalent to medium grit
sandpaper) on the leading edges or upper wing surfaces can cause
significant reduction in the stall angle-of-attack. This can increase
stall speed up to 30 knots. The increased stall speed can be well above
the stall warning (stick shaker) activation speed.

Takeoff shall not be attempted unless the pilot-in-command has ensured
that the aircraft surfaces are free of ice, frost, and snow
accumulation, as required by §§ 91.527 and 121.629 of the Federal
Aviation Regulations (FAR).

In addition, takeoff shall not be attempted when the Outside Air
Temperature (OAT) is below 6 degrees C (Centigrade) \[42 degrees F
(Fahrenheit)\]; and either the difference between the dew point
temperature and OAT is less than 3 degrees C (5 degrees F), or visible
moisture (rain, drizzle, sleet, snow, fog, etc.) is present, unless the
operator complies with either Option 1 or Option 2 below:

**Option 1**

The leading edge and upper wing surfaces have been physically checked
for ice/frost/snow and the flight crew verifies that a visual check and
a physical (hands-on) check of the leading edge and upper wing surfaces
has been accomplished and that the wing is clear of ice/frost/snow
accumulation; or

**Option 2**

The following takeoff procedure is used:

**Warning**

The following technique cannot be used unless the pilot-in-command has
ensured that the aircraft surfaces are free of ice, frost, and snow, as
required by §§ 91.527 and 121.629 of the FAR.

-   (All Marks, except Mark 0100 and Mark 0070) When using flight
    director for takeoff, select HDG mode and 10 degrees pitch attitude.

```{=html}
<!-- -->
```
-   Select the largest flap setting that is permissible for the takeoff
    weight/altitude/temperature conditions.

```{=html}
<!-- -->
```
-   (All Marks, except Mark 0100 and Mark 0070) Use rated takeoff
    thrust.

```{=html}
<!-- -->
```
-   (Mark 0100 and Mark 0070) Use takeoff/go-around (TOGA) thrust.

```{=html}
<!-- -->
```
-   Do not use flexible thrust.

```{=html}
<!-- -->
```
-   At V~R~ rotate slowly (less than 3 degrees per second) to 10 degrees
    pitch attitude.

```{=html}
<!-- -->
```
-   When positively climbing, select gear UP.

```{=html}
<!-- -->
```
-   Do not exceed 10 degrees pitch until airspeed is above V~2~ + 20
    KTS.

```{=html}
<!-- -->
```
-   When above V~2~ + 20 KTS, slowly increase the pitch attitude,
    keeping the speed above V~2~ + 20 KTS.

```{=html}
<!-- -->
```
-   Retract the flaps at or above V~FR~ + 20 KTS.

*Notes to Option 2*

1\. The available field length must be greater than or equal to 120
percent of the takeoff distance required by regulation for the actual
gross weight. Also, the 20 percent increase in takeoff distance must be
accounted for in the obstacle clearance analysis. Weight must be
off-loaded, if necessary, to meet these conditions.

2\. (Mark 0100 and Mark 0070) Do not follow the Flight Director pitch
command during rotation for takeoff and initial climb, as this will
result in exceeding the recommended maximum pitch angle of 10 degrees
before reaching the speed of V~2~ + 20 KTS.

3\. (Mark 0100 and Mark 0070) Do not engage the autopilot until leaving
the Automated Flight Control and Augmentation System (AFCAS) takeoff
(TO) mode.

4\. For the case of an engine failure, refer to the applicable procedure
in Section 4.17.01 Single Engine Operation of the F.28 Mark 0100 (Fokker
100) and F.28 Mark 0070 (Fokker 70) AFM, or Section 1.7.4 Operation
Under Abnormal Conditions of the F.28 FHB, as applicable.

5\. During takeoff, the first indication of wing contamination will
probably be airframe buffet when the pitch angle is increased above 10
degrees, followed by wing drop and insufficient climb rate. Do not
exceed 10 degrees pitch until airspeed is above V~2~ + 20 KTS."

This action is required until the requirements of paragraph (c) of this
AD are accomplished, or the actions specified in paragraphs (d) and (e)
of this AD are accomplished.

**Note 2:** If an operator elects to implement in its fleet only one of
the two options specified in this paragraph, the other OPTION does not
have to be included in the Limitations Section of the AFM. However, the
OPTION that is implemented must be incorporated in the AFM verbatim as
it appears in this paragraph.

**New Requirements of This AD**

*Modification*

\(b\) Except as provided in paragraph (d) of this AD: Within 18 months
after the effective date of this AD, modify the wing anti-ice system for
operation on the ground as specified in paragraph (b)(1) or (b)(2) of
this AD, as applicable.

\(1\) For Model F.28 Mark 0070 and 0100 series airplanes, modify in
accordance with Fokker Service Bulletin SBF100--30--018, Revision 1,
Appendix I, Appendix 1, dated August 14, 1999.

\(2\) For Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes,
modify in accordance with Fokker Service Bulletin F28/30--031, Appendix
I, Revision 1, dated May 4, 1998; and Fokker Proforma Service Bulletin
F.28/30--032, including Appendix 1, dated December 1, 1999; as
applicable.

*Manual Change Notification (MCNO)*

\(c\) Prior to further flight after accomplishing the modification
required by paragraph (b) of this AD, remove the AFM revisions required
by paragraph (a) of this AD, and incorporate the flight manual changes
specified in Fokker MCNO F100--003, dated September 19, 1997 (for Fokker
Model F.28 Mark 070 and 0100 series airplanes); and Fokker MCNO
F28--003, dated September 5, 1997 (for Fokker Model F.28 Mark 1000,
2000, 3000, and 4000 series airplanes); as applicable. Accomplishment of
the actions specified in paragraphs (b) and (c) of this AD constitute
terminating action for the requirements of this AD.

**Note 3:** Incorporation of the leading edge thermal anti-ice
modification and associated operating instructions does not relieve the
requirement that airplane surfaces are free of ice, frost, and snow
accumulation as required by §§ 91.527 and 121.629 of the Federal
Aviation Regulations (14 CFR 91.527 and 121.629).

*Acceptable Method of Compliance With the Requirements of Paragraphs (b)
and (c) of This AD*

\(d\) For Fokker Model F.28 Mark 0100 series airplanes on which a
"Contaminant/Fluid Integrity Measuring System" (C/FIMS") has been
installed in accordance with Supplemental Type Certification ST291CH, as
amended on August 20, 1998: Prior to further flight after accomplishment
of STC ST291CH, as amended on August 20, 1998, remove the AFM revisions
required by paragraph (a) of this AD, and incorporate the following into
the Limitations Section of the FAA-approved AFM (This may be
accomplished by inserting a copy of this AD in the AFM):

"Wing De-Icing/Anti-Icing Prior To Takeoff

Caution

The Model F.28 series airplane has a wing design with no leading edge
high lift devices, such as slats. Wings without leading edge high lift
devices are particularly susceptible to loss of lift due to wing icing.
Minute amounts of ice or other contamination (equivalent to medium grit
sandpaper) on the leading edges or upper wing surfaces can cause
significant reduction in the stall angle-of-attack. This can increase
stall speed up to 30 knots. The increased stall speed can be well above
the stall warning (stick shaker) activation speed.

Takeoff shall not be attempted unless the pilot-in-command has ensured
that the aircraft surfaces are free of ice, frost, and snow
accumulation, as required by §§ 91.527 and 121.629 of the Federal
Aviation Regulations (FAR).

In addition, takeoff shall not be attempted when the Outside Air
Temperature (OAT) is below 6 degrees C (Centigrade) \[42 degrees F
(Fahrenheit)\]; and either the difference between the dew point
temperature and OAT is less than 3 degrees C (5 degrees F), or visible
moisture (rain, drizzle, sleet, snow, fog, etc.) is present; unless the
operator complies with Option 1, Option 2, or Option 3.

**Option 1**

\(i\) Operate the C/FIMS" in accordance with AFM Supplement AlliedSignal
Aerospace Canada Document Number 6C--486, Revision 2, dated August 4,
1999.

\(ii\) C/FIMS" is an advisory system that must not be used as the
primary means of determining whether the airplane should be initially
deiced or anti-iced or used as the primary means of determining that the
fluid has failed.

\(iii\) C/FIMS" may be used only for the time periods covered by the
dicing/anti-icing holdover time tables. C/FIMS" may not be used when the
holdover time tables have been exceeded; or

If the C/FIMS^TM^ is not operational:

**Option 2**

The leading edge and upper wing surfaces have been physically checked
for ice/frost/snow and the flight crew verifies that a visual check and
a physical (hands-on) check of the leading edge and upper wing surfaces
has been accomplished and that the wing is clear of ice/frost/snow
accumulation; or

If the C/FIMS^TM^ is not operational:

**Option 3**

The following takeoff procedure is used:

Warning

The following technique cannot be used unless the pilot-in-command has
ensured that the aircraft surfaces are free of ice, frost, and snow, as
required by §§ 91.527 and 121.629 of the FAR.

-   Select the largest flap setting that is permissible for the takeoff
    weight/altitude/temperature conditions.

```{=html}
<!-- -->
```
-   Use takeoff/go-around (TOGA) thrust.

```{=html}
<!-- -->
```
-   Do not use flexible thrust.

```{=html}
<!-- -->
```
-   At VR rotate slowly (less than 3 degrees per second) to 10 degrees
    pitch attitude.

```{=html}
<!-- -->
```
-   When positively climbing, select gear UP.

```{=html}
<!-- -->
```
-   Do not exceed 10 degrees pitch until airspeed is above V~2~ + 20
    KTS.

```{=html}
<!-- -->
```
-   When above V~2~ + 20 KTS, slowly increase the pitch attitude,
    keeping the speed above V~2~ + 20 KTS.

```{=html}
<!-- -->
```
-   Retract the flaps at or above V~FR~ + 20 KTS.

*Notes to Option 3*

1\. The available field length must be greater than or equal to 120
percent of the takeoff distance required by regulation for the actual
gross weight. Also, the 20 percent increase in takeoff distance must be
accounted for in the obstacle clearance analysis. Weight must be
off-loaded, if necessary, to meet these conditions.

2\. Do not follow the Flight Director pitch command during rotation for
takeoff and initial climb, as this will result in exceeding the
recommended maximum pitch angle of 10 degrees before reaching the speed
of V~2~ + 20 KTS.

3\. Do not engage the autopilot until leaving the Automated Flight
Control and Augmentation System (AFCAS) takeoff (TO) mode.

4\. For the case of an engine failure, refer to the applicable procedure
in Section 4.17.01 Single Engine Operation of the F.28 Mark 0100 (Fokker
100) AFM.

5\. During takeoff, the first indication of wing contamination will
probably be airframe buffet when the pitch angle is increased above 10
degrees, followed by wing drop and insufficient climb rate. Do not
exceed 10 degrees pitch until airspeed is above V~2~ + 20 KTS."

Accomplishment of the actions specified in this paragraph after the
installation of STC ST291CH, as amended on August 20, 1998, constitute
terminating action for the requirements of this AD.

**Note 4:** Operators should note that, while Option 1 specified in
paragraph (d) of this AD must be incorporated into the Limitations
Section of the AFM, operators may elect to incorporate either both or
only one of the other two options specified in paragraph (d) of this AD.
Only Option 1 and the elected option(s) need to be incorporated into the
AFM. However, any option that is incorporated into the AFM must be
identical to the option wording specified in paragraph (d) of this AD.

**Note 5:** Installation of the Contaminant/Fluid Integrity Measuring
System (C/FIMS ^TM^) in accordance with Supplemental Type Certification
ST291CH, as amended on August 20, 1998, and accomplishment of the
actions specified in paragraph (d) of this AD, do not relieve the
requirement that airplane surfaces are free of ice, frost, and snow
accumulation as required by §§ 91.527 and 121.629 of the Federal
Aviation Regulations (14 CFR 91.527 and 121.629).

**Alternative Methods of Compliance**

\(e\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, International Branch, ANM--116. Operators
shall submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, International Branch, ANM--116.

**Note 6:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the
International Branch, ANM--116.

**Special Flight Permits**

\(f\) 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 accomplished.

**Incorporation by Reference**

\(g\) The actions required by paragraphs (b) and (c) of this AD shall be
done in accordance with Fokker Service Bulletin SBF100--30--018,
Appendix I, Revision 1, dated August 14, 1999; Fokker Service Bulletin
F28/30--031, Appendix I, Revision 1, dated May 4, 1998; Fokker Proforma
Service Bulletin F28/30--032, including Appendix 1, dated December 1,
1999; Fokker Manual Change Notification MCNO F100--003, dated September
19, 1997; and Fokker Manual Change Notification MCNO F28--003, dated
September 5, 1997. 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 Fokker Services B.V., P.O.
Box 231, 2150 AE Nieuw-Vennep, The Netherlands. Copies may be inspected
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW.,
Renton, Washington; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.

**Effective Date**

\(h\) This amendment becomes effective on August 29, 2002.

**FOR FURTHER INFORMATION CONTACT:** Tom Rodriguez, Aerospace Engineer,
International Branch, ANM--116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055--4056; telephone (425)
227--1137; fax (425) 227--1149.

Issued in Renton, Washington, on July 12, 2002.

Lirio Liu-Nelson,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02--18624 Filed 7--24--02; 8:45 am\]

BILLING CODE 4910--13--U

**BW 2002-15**

**HAMILTON SUNDSTRAND POWER SYSTEMS**

**AIRWORTHINESS DIRECTIVE**

**APPLIANCE**

**LARGE AIRCRAFT**

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

**Applicability**

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

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

**Compliance**

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

To replace affected compressor wheels

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

**Cast Steel Compressor Wheel Replacement**

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

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

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

**Wrought Steel Compressor Wheel Replacement**

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

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

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

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

**Reduced Life Limits**

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

**Alternative Methods of Compliance**

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

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

**Special Flight Permits**

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

**Effective Date**

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

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

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

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

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

BILLING CODE 4910-13-P

**BW 2002-15**

**HAMILTON SUNDSTRAND CORPORATION**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002--15--03 Hamilton Sundstrand Corporation:** Amendment 39--12831.
Docket No. 2002--NE--02--AD. Supersedes AD 2002--05--51.

**Applicability:** This airworthiness directive (AD) is applicable to
Hamilton Sundstrand Corporation (formerly Hamilton Standard Division)
model 568F--1 propellers installed with blades, part numbers (P/N\'s)
R815505--2 and R815505--3, that have a serial number (SN) of FR1698 or
lower. These propellers are installed on, but not limited to,
Aerospatiale ATR 42--400 and --500 and ATR 72 airplanes.

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

**Compliance**

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

To prevent blade failure due to corrosion-induced fatigue, which could
result in blade separation and possible loss of airplane control, do the
following:

\(a\) For propeller blades P/N\'s R815505--2 and R815505--3, replace
propeller blades SN FR265 or lower before further flight.

\(b\) Before further flight, replace propeller blades P/N\'s R815505--2
and R815505--3, that have a SN of FR1698 or lower, installed on ATR 72
and ATR 42--400 airplanes.

\(c\) After the effective date of this AD, do not install any propeller
blade that was removed in accordance with paragraph (b) of this AD on
any airplane.

\(d\) Replace propeller blades P/N\'s R815505--2 and R815505--3, that
have a SN of FR1698 or lower, installed on ATR 42--500 airplanes, before
December 31, 2002.

\(e\) After the effective date of this AD, do not install any propeller
blades, P/N\'s R815505--2 and R815505--3, that have a SN of FR1698 or
lower, on any airplane unless an ultrasonic shear wave inspection of the
blade tulip is done in accordance with the Accomplishment Instructions
of Hamilton Sundstrand ASB 568F--61--A35, Revision 2, dated March 21,
2002, before installation of the propeller blade.

\(f\) Procedures for removing the propeller blade and installing a
serviceable blade can be found in Hamilton Sundstrand Maintenance Manual
P5206.

\(g\) Within 50 FH since-last-inspection, for propeller blades, P/N\'s
R815505--2 and R815505--3, that have a SN of FR1698 or lower, perform an
ultrasonic shear wave inspection of the blade tulip in accordance with
the Accomplishment Instructions of Hamilton Sundstrand ASB
568F--61--A35, Revision 2, dated March 21, 2002, and remove blades with
unacceptable indications in accordance with the ASB.

\(h\) Thereafter, within 50 FH since-last-inspection, for propellers
blades P/N\'s R815505--2 and R815505--3, that have a SN of FR1698 or
lower, perform an ultrasonic shear wave inspection of the blade tulip in
accordance with the Accomplishment Instructions of Hamilton Sundstrand
ASB 568F--61--A35, Revision 2, dated March 21, 2002, and remove blades
with unacceptable indications in accordance with the ASB.

**Optional Terminating Action**

\(i\) Replacement of propeller blades, P/N R815505--2, with propeller
blades, P/N R81505R2; or propeller blades, P/N R815505--3, with
propeller blades, P/N R815505R3, constitutes terminating action for the
repetitive inspection requirements specified in paragraph (h) of this
AD.

**Alternative Methods of Compliance**

\(j\) 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 (ACO).
Operators must submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send it
to the Manager, Boston ACO.

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

**Special Flight Permits**

\(k\) Special limited 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) for a nonrevenue flight to a location where the requirements of
this AD can be done.

**Documents That Have Been Incorporated By Reference**

\(l\) The actions required by this AD must be done in accordance with
Hamilton Sundstrand Alert Service Bulletin No. 568F--61--A35, Revision
2, dated March 21, 2002. 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 Hamilton Sundstrand
Propeller Technical Team,

One Hamilton Road, Mail Stop 1--3--AB43, Windsor Locks, CT 06096--1010,
U.S.A.; Fax 1--860--654--5107. Copies may be inspected, by appointment,
at the FAA, New England Region, Office of the Regional Counsel, 12 New
England Executive Park, Burlington, MA; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

**Effective Date**

\(m\) This amendment becomes effective August 9, 2002.

**FOR FURTHER INFORMATION CONTACT:** Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803--5299;
telephone (781) 238--7158; fax (781) 238--7170.

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

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

\[FR Doc. 02--18481 Filed 7--24--02; 8:45 am\]

BILLING CODE 4910--13--P