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# **FEDERAL AVIATION ADMINISTRATION**

## **AIRWORTHINESS DIRECTIVES**

**LARGE AIRCRAFT**

**BIWEEKLY 2002-12**

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

U.S. Department of Transportation

### Federal Aviation Administration

Regulatory Support Division

Delegation and Airworthiness Programs Branch, AIR-140

P. O. Box 26460

Oklahoma City, OK 73125-0460

FAX 405-954-4104

Biweekly 2002-01

  ------------ ---------- ----------------- ----------------------------------
  2001-23-12   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     |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | DC-9-31                         |
| -08-09 |         | Douglas        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 747 Series                      |
| -08-10 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
|        |         |                |                                 |
+--------+---------+----------------+---------------------------------+
|        |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| **Bi   |         |                |                                 |
| weekly |         |                |                                 |
| 2      |         |                |                                 |
| 002-09 |         |                |                                 |
| conti  |         |                |                                 |
| nued** |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 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) Seires

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

**BW 2002-12**

**BOMBARDIER, INC.**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-08-19 Bombardier, Inc. (Formerly Canadair):** Amendment 39-12731.
Docket 2002-NM-99-AD. Supersedes AD 2002-06-51, Amendment 39-12688.

**Applicability:** Model CL-600-2C10 (Regional Jet Series 700 and 701)
series airplanes, serial numbers 10005 and subsequent; 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 (k) 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 flight crew has the procedures necessary to address
uncommanded fuel transfer between the wing fuel tanks and the center
fuel tank; and to detect and correct discrepancies in the fuel
distribution system for the center tank, which could cause the center
tank to overfill and fuel to leak from the center tank vent system or to
become inaccessible, and could result in engine fuel starvation;
accomplish the following:

**Restatement of Requirements of AD 2002-06-51**

**Revision of Airplane Flight Manual (AFM)**

\(a\) For airplanes having serial numbers 10005 through 10039: Within 2
days after April 2, 2002 (the effective date of AD 2002-06-51, amendment
39-12688), revise the Limitations and Abnormal Procedures sections of
Canadair Regional Jet Series 700 of FAA-approved AFM CSP B-012 to
include the following information included in paragraphs (a)(1) and
(a)(2) of this AD (this may be accomplished by inserting a copy of this
AD into the AFM):

\(1\) Revise the \"Limitations--Power Plant,\'\' Paragraph 6, \"Fuel\'\'
to include the following information, per Canadair Temporary Revision
(TR) RJ 700/23-1, dated March 7, 2002:

\"Dispatch with the fuel quantity gauging system inoperative is
prohibited.\'\'

\(2\) Revise the \"Abnormal Procedures--Fuel,\'\' Paragraph H, \"L or R
Main Ejector\'\' to include the following information, per Canadair TR
RJ 700/23-1, dated March 7, 2002:

+---------------------------------------------+------------------------+
| **\"H. L or R MAIN EJECTOR**                |                        |
+---------------------------------------------+------------------------+
| > \(1\) Left and right boost pumps          | Confirm operating      |
+---------------------------------------------+------------------------+
| > \(2\) Affected engine instruments         | Monitor                |
+---------------------------------------------+------------------------+
| > \(3\) Fuel tank quantity                  | Monitor and balance,   |
|                                             | if required            |
+---------------------------------------------+------------------------+
| > **If centre tank quantity increases       |                        |
| > abnormally (by more than 227 kg (500      |                        |
| > lb)):**                                   |                        |
+---------------------------------------------+------------------------+
| > \(4\) Land at the nearest suitable        |                        |
| > airport                                   |                        |
+---------------------------------------------+------------------------+
| > **If centre tank quantity continues to    |                        |
| > increase (by more than 454 kg (1000       |                        |
| > lb)):**                                   |                        |
+---------------------------------------------+------------------------+
| > \(5\) Affected engine thrust              | IDLE                   |
+---------------------------------------------+------------------------+
| > \(6\) Consider shutting down affected     |                        |
| > engine to prevent centre tank transfer.   |                        |
|                                             |                        |
| -   Ensure both BOOST PUMPs are operating.  |                        |
+---------------------------------------------+------------------------+
| > **If centre tank quantity further         |                        |
| > continues to increase (by more than 680   |                        |
| > kg (1500 lb)):**                          |                        |
+---------------------------------------------+------------------------+
| > \(7\) Land immediately at the nearest     |                        |
| > suitable airport.\'\'                     |                        |
+---------------------------------------------+------------------------+

**Revision of Minimum Equipment List (MEL)**

\(b\) For airplanes having serial numbers 10005 through 10039: Within 2
days after April 2, 2002, remove the relieving requirements specified in
MEL CL-600-2C10 for the following items:

\(1\) Transfer Ejectors (Center Tank) (Ref. Master Minimum Equipment
List (MMEL) Item 28-13-07).

\(2\) Fuel Transfer shutoff valves (SOV) (Center Tank) (Ref. MMEL Item
28-13-08).

\(3\) Xflow Pump (Ref. MMEL Item 28-13-10).

\(4\) Engine Indication and Crew Alerting System (EICAS) Fuel Tank
Quantity Readouts (Left, Right, and Total) (Ref. MMEL Item 28-41-01).

\(5\) EICAS Center and Total Fuel Tank Quantity Readouts (Ref. MMEL Item
28-41-02).

\(6\) Fuel Computer Channels (Ref. MMEL Item 28-41-03).

**Operational Limitation**

\(c\) For airplanes having serial numbers 10005 through 10039: Within 2
days after April 2, 2002, revise the Limitations section of Canadair
Regional Jet Series 700 of FAA-approved AFM CSP B-012 to limit operation
of the airplane to flight within 60 minutes of a suitable alternative
airport. This action may be accomplished by inserting a copy of this AD
into the Limitations section of the AFM.

**Operational Requirements**

\(d\) For airplanes having serial numbers 10005 through 10039: Within 2
days after April 2, 2002, revise the Limitations section of Canadair
Regional Jet Series 700 of FAA-approved AFM CSP B-012 to specify that,
prior to each further flight, the normal mission fuel requirements are
increased by 3,000 pounds. This action may be accomplished by inserting
a copy of this AD into the Limitations section of the AFM.

**New Requirements of This AD**

**Revision of Airplane Flight Manual (AFM)**

\(e\) For airplanes other than those identified in paragraph (a) of this
AD: Within 2 days after the effective date of this AD, revise the
Limitations and Abnormal Procedures sections of Canadair Regional Jet
Series 700 of FAA-approved AFM CSP B-012 to include the following
information included in paragraphs (e)(1) and (e)(2) of this AD (this
may be accomplished by inserting a copy of this AD into the AFM):

\(1\) Revise the \"Limitations--Power Plant,\'\' Paragraph 6, \"Fuel\'\'
to include the following information, per Canadair Temporary Revision
(TR) RJ 700/23-1, dated March 7, 2002:

\"Dispatch with the fuel quantity gauging system inoperative is
prohibited.\'\'

\(2\) Revise the \"Abnormal Procedures--Fuel,\'\' Paragraph H, \"L or R
Main Ejector\'\' to include the following information, per Canadair TR
RJ 700/23-1, dated March 7, 2002:

+-------------------------------------------------------+--------------+
| **\"H. L or R MAIN EJECTOR**                          |              |
+-------------------------------------------------------+--------------+
| > \(1\) Left and right boost pumps                    | Confirm      |
|                                                       | operating    |
+-------------------------------------------------------+--------------+
| > \(2\) Affected engine instruments                   | Monitor      |
+-------------------------------------------------------+--------------+
| > \(3\) Fuel tank quantity                            | Monitor and  |
|                                                       | balance, if  |
|                                                       | required     |
+-------------------------------------------------------+--------------+
| > **If centre tank quantity increases abnormally (by  |              |
| > more than 227 kg (500 lb)):**                       |              |
+-------------------------------------------------------+--------------+
| > \(4\) Land at the nearest suitable airport.         |              |
+-------------------------------------------------------+--------------+
| > **If centre tank quantity continues to increase (by |              |
| > more than 454 kg (1000 lb)):**                      |              |
+-------------------------------------------------------+--------------+
| > \(5\) Affected engine thrust                        | IDLE         |
+-------------------------------------------------------+--------------+
| > \(6\) Consider shutting down affected engine to     |              |
| > prevent centre tank transfer.                       |              |
+-------------------------------------------------------+--------------+
| -   Ensure both BOOST PUMPs are operating.            |              |
+-------------------------------------------------------+--------------+
| > **If centre tank quantity further continues to      |              |
| > increase (by more than 680 kg (1500 lb)):**         |              |
+-------------------------------------------------------+--------------+
| > \(7\) Land immediately at the nearest suitable      |              |
| > airport.\'\'                                        |              |
+-------------------------------------------------------+--------------+

**Revision of Minimum Equipment List (MEL)**

\(f\) For airplanes other than those identified in paragraph (b) of this
AD: Within 2 days after the effective date of this AD, remove the
relieving requirements specified in MEL CL-600-2C10 for the following
items.

\(1\) Transfer Ejectors (Center Tank) (Ref. Master Minimum Equipment
List (MMEL) Item 28-13-07).

\(2\) Fuel Transfer shutoff valves (SOV) (Center Tank) (Ref. MMEL Item
28-13-08).

\(3\) Xflow Pump (Ref. MMEL Item 28-13-10).

\(4\) Engine Indication and Crew Alerting System (EICAS) Fuel Tank
Quantity Readouts (Left, Right, and Total) (Ref. MMEL Item 28-41-01).

\(5\) EICAS Center and Total Fuel Tank Quantity Readouts (Ref. MMEL Item
28-41-02).

\(6\) Fuel Computer Channels (Ref. MMEL Item 28-41-03).

**Operational Limitation**

\(g\) For airplanes other than those identified in paragraph (c) of this
AD: Within 2 days after the effective date of this AD, revise the
Limitations section of Canadair Regional Jet Series 700 of FAA-approved
AFM CSP B-012 to limit operation of the airplane to flight within 60
minutes of a suitable alternative airport. This action may be
accomplished by inserting a copy of this AD into the Limitations section
of the AFM.

**Operational Requirements**

\(h\) For airplanes other than those identified in paragraph (d) of this
AD: Within 2 days after the effective date of this AD, revise the
Limitations section of Canadair Regional Jet Series 700 of FAA-approved
AFM CSP B-012 to specify that, prior to each further flight, the normal
mission fuel requirements are increased by 3,000 pounds. This action may
be accomplished by inserting a copy of this AD into the Limitations
section of the AFM.

**Modification**

\(i\) For airplanes having serial numbers 10005 through 10039 inclusive:
Within 200 flight hours after the effective date of this AD, modify the
fuel distribution system for the center tank per CRJ700 (Bombardier)
Alert Service Bulletin A670BA-28-007, Revision B, dated March 18, 2002.

\(1\) Install new brackets, part numbers (P/N) KBA670-62010-1 and P/N
KBA670-62010-2; and attach ejectors with new P-clamps.

\(2\) Replace existing couplings (four in total), P/N B0305025A24, with
new couplings, P/N B0305072-24DE.

\(3\) Relocate brackets, P/N CC670-62278-1 and P/N CC670-62278-2.

**Note 2:** Modifications accomplished prior to the effective date of
this AD per CRJ700 (Bombardier) Alert Service Bulletin A670BA-28-007,
original issue, dated March 12, 2002; or Revision A, dated March 15,
2002; are considered acceptable for compliance with the applicable
action specified in this AD.

**Inspection and Corrective Actions**

\(j\) For airplanes having serial numbers 10005 and subsequent:
Accomplish a one-time detailed inspection of the motive flow line and
fuel feed line in the fuel distribution system for the center tank to
detect any discrepancy (including misalignment, pre-loading, or damage)
per CRJ700 (Bombardier) Alert Service Bulletin A670BA-28-005, Revision
B, dated March 21, 2002, including Appendix A, dated February 8, 2002;
at the time specified in paragraph (j)(1) or (j)(2) of this AD, as
applicable. If any discrepancy is found, before further flight, replace
any part that exceeds the limit in the alert service bulletin; and
correct any misalignment of parts; per the alert service bulletin.

\(1\) For airplanes on which the detailed inspection required by
paragraph (j) of this AD has been accomplished per CRJ700 (Bombardier)
Alert Service Bulletin A670BA-28-005, original issue, dated February 8,
2002; or Revision A, dated March 12, 2002; prior to the effective date
of this AD: Do the inspection within 400 flight hours after performing
the most recent detailed inspection, or within 200 flight hours after
the effective date of this AD, whichever occurs later.

\(2\) For airplanes other than those identified in paragraph (j)(1) of
this AD: Do the inspection within 400 flight hours after the effective
date of this AD.

**Note 3:** 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.\'\'

**Alternative Methods of Compliance**

\(k\) 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, New York 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, New York ACO.

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

**Special Flight Permits**

\(l\) 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. The operational limitations and
requirements of paragraphs (c) and (d) of this AD will be applicable to
all special flight permits.

**Incorporation by Reference**

\(m\) Except as provided by paragraphs (a) through (h) of this AD, the
actions shall be done in accordance with Canadair Temporary Revision RJ
700/23-1, dated March 7, 2002; CRJ700 (Bombardier) Alert Service
Bulletin A670BA-28-005, Revision B, dated March 21, 2002, including
Appendix A, dated February 8, 2002; and CRJ700 (Bombardier) Alert
Service Bulletin A670BA-28-007, Revision B, dated March 18, 2002; as
applicable. CRJ700 (Bombardier) Alert Service Bulletin A670BA-28-005,
Revision B, dated March 21, 2002, contains the following list of
effective pages:

  ----------------------------- ------------------------ -----------------
  **Page number**               **Revision level shown   **Date shown on
                                on page**                page**

  1-36                          B                        March 21, 2002.

  **Appendix A**                                         

  A1, A2                        Original                 February 8, 2002.
  ----------------------------- ------------------------ -----------------

(The manufacturer\'s name is indicated only on page 1 of the service
bulletins; no other pages of these documents contain this information.)
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 Bombardier, Inc., Canadair Aerospace Group,
P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C3G9, Canada.
Copies may be inspected at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft
Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New
York; 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 Canadian
airworthiness directive CF-2002-22, dated March 22, 2002.

**Effective Date**

\(n\) This amendment becomes effective on May 28, 2002.

**FOR FURTHER INFORMATION CONTACT:** James Delisio, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New
York 11581; telephone (516) 256-7521; fax (516) 568-2716.

Issued in Renton, Washington, on May 7, 2002.

Ali Bahrami,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-11942 Filed 5-10-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**AIRBUS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-11-04 Airbus Industrie:** Amendment 39-12765. Docket
99-NM-322-AD. Supersedes AD 97-16-06, Amendment 39-10097.

**Applicability:** All Model A300 B4-600 and A300 B4-600R series
airplanes, and all Model A300 F4-605R 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 (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 fatigue cracking of the forward fitting of fuselage frame
FR47, which could result in reduced structural integrity of the frame,
accomplish the following:

**Inspections**

\(a\) Perform a rotating probe inspection to detect cracking of the
applicable attachment holes on the left and right internal angles of the
wing center box, in accordance with Airbus Service Bulletin
A300-57-6049, Revision 4, dated July 27, 2000. Do the inspection at the
applicable time specified by paragraph 1.A.(2), Planning Information, of
the service bulletin, except as required by paragraph (e) of this AD.
Repeat the inspection thereafter at intervals not to exceed the
applicable interval specified in the service bulletin, except that all
touch-and-go landings must be counted in determining the total number of
flight cycles between consecutive inspections.

\(1\) If no cracking is found: Prior to further flight, install new
fasteners in accordance with the service bulletin.

\(2\) If any cracking is found: Prior to further flight, perform
applicable corrective actions (including reaming, drilling,
drill-stopping holes, chamfering, performing follow-on inspections, and
installing new or oversize fasteners) in accordance with the service
bulletin, except as required by paragraph (d) of this AD.

\(b\) Perform a rotating probe inspection to detect cracking of the
applicable attachment holes in the horizontal flange of the internal
corner angle fitting of frame FR47, in accordance with Airbus Service
Bulletin A300-57-6086, dated June 6, 2000. Do the inspection at the
applicable time specified by the service bulletin, except as required by
paragraph (e) of this AD. Repeat the inspection thereafter at intervals
not to exceed the applicable interval specified in the service bulletin,
except that all touch-and-go landings must be counted in determining the
total number of flight cycles between consecutive inspections.

\(1\) If no cracking is detected: Prior to further flight, install new
fasteners in accordance with the service bulletin.

\(2\) If any cracking is detected: Prior to further flight, perform
applicable corrective actions (including inspecting hole T, reaming the
holes, and installing oversize fasteners) in accordance with the service
bulletin, except as required by paragraph (d) of this AD.

**Modification**

\(c\) Modify the left and right internal angle fittings of the wing
center box. The modification includes performing a rotating probe
inspection to detect cracking, repairing cracks, cold expanding holes,
and installing medium interference fitting bolts. Perform the
modification in accordance with and at the applicable time specified by
paragraph 1.B.(4), Accomplishment Timescale, of Airbus Service Bulletin
A300-57-6050, Revision 02, dated February 10, 2000; except as required
by paragraphs (d) and (e) of this AD.

**Note 2:** Modification prior to the effective date of this AD in
accordance with Airbus Service Bulletin A300-57-6050, dated September 9,
1994, or Revision 01, dated May 31, 1999, is acceptable for compliance
with the requirements of paragraph (c) of this AD.

**Exceptions to Specifications in Service Bulletins**

\(d\) If any crack is detected during any inspection required by
paragraph (b) or (c) of this AD, and the applicable service bulletin
specifies to contact the manufacturer for disposition of certain
corrective actions: Prior to further flight, repair in accordance with a
method approved by either the Manager, International Branch, ANM-116,
FAA, Transport Airplane Directorate, or the Direction Generale de
l\'Aviation Civile (DGAC) (or its delegated agent).

\(e\) Where the service bulletins specified in paragraphs (a), (b), and
(c) of this AD specify a grace period relative to receipt of the service
bulletin, this AD requires compliance within the applicable grace period
following the effective date of this AD, if the threshold has been
exceeded.

**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, 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.

\(2\) Alternative methods of compliance, approved previously in
accordance with AD 97-16-06, amendment 39-10097, are approved as
alternative methods of compliance with the applicable requirements of
this AD.

**Note 3:** 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**

\(g\) 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**

\(h\) Except as required by paragraph (d) of this AD: The actions shall
be done in accordance with Airbus Service Bulletin A300-57-6049,
Revision 4, dated July 27, 2000; Airbus Service Bulletin A300-57-6086,
dated June 6, 2000; and Airbus Service Bulletin A300-57-6050, Revision
02, dated February 10, 2000; as applicable. Revision 02 of Airbus
Service Bulletin A300-57-6050 contains the following effective pages:

+-----------------------------------+----------------+----------------+
| > **Page number**                 | > **Revision   | > **Date shown |
|                                   | > level shown  | > on page**    |
|                                   | > on page**    |                |
+-----------------------------------+----------------+----------------+
| > 1, 4, 8, 9, 17--32, 41, 42, 57, | > 02           | > February 10, |
| > 58, 61--63, 75, 77              |                | > 2000.        |
+-----------------------------------+----------------+----------------+
| > 2, 3, 5--7, 10--12, 33, 34, 37, | > 01           | > May 31,      |
| > 38, 47, 59, 60, 76              |                | > 1999.        |
+-----------------------------------+----------------+----------------+
| > 13--16, 35, 36, 39, 40, 43--46, | > Original     | > September 9, |
| > 48--56, 64--74                  |                | > 1994.        |
+-----------------------------------+----------------+----------------+

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 Airbus Industrie, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France. 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.

**Note 4:** The subject of this AD is addressed in French airworthiness
directive 2000-533-328(B), dated December 27, 2000.

**Effective Date**

\(i\) This amendment becomes effective on July 8, 2002.

**FOR FURTHER INFORMATION CONTACT:** Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.

Issued in Renton, Washington, on May 22, 2002.

Ali Bahrami,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-13422 Filed 5-31-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**BOEING**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-11-06 Boeing:** Amendment 39-12767. Docket 2001-NM-35-AD.
Supersedes AD 2000-19-08, Amendment 39-11909.

**Applicability:** Model 777 series airplanes, line numbers 1 through
369 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 (h)(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 detect and correct cracking or missing pieces of the cove skin, or
undersized seal inserts installed in the spanwise bulb seals, on the
outboard leading edge slats on the wings, which could result in skin
separation or structural damage to the leading edge slats and consequent
reduced controllability of the airplane, accomplish the following:

**Restatement of Requirements of AD 2000-19-08**

**Inspection**

\(a\) For airplanes having line numbers 2 through 265 inclusive: At the
applicable time specified by paragraph (a)(1) or (a)(2) of this AD,
perform detailed inspections to detect cracking of the cove skin on the
outboard leading edge slats of the left and right wings at slat numbers
1 through 6 inclusive, and 9 through 14 inclusive; in accordance with
Boeing Alert Service Bulletin 777-57A0034, Revision 2, dated November
19, 1998; Revision 3, dated May 4, 2000; Revision 4, dated July 20,
2000; or Revision 5, dated January 25, 2001. Repeat the inspections
thereafter at intervals not to exceed 100 flight cycles or 400 flight
hours, whichever occurs first.

\(1\) For airplanes on which the repetitive inspections required by
paragraph (a) of AD 99-04-19 HAVE been initiated prior to October 10,
2000 (the effective date of AD 2000-19-08, amendment 39-11909): Inspect
at the earlier of the times specified by paragraphs (a)(1)(i) and
(a)(1)(ii) of this AD.

\(i\) Within 350 flight cycles after the most recent inspection.

\(ii\) At the later of the times specified by paragraphs (a)(1)(ii)(A)
and (a)(1)(ii)(B) of this AD.

\(A\) Within 100 flight cycles or 400 flight hours, whichever occurs
first, after the most recent inspection.

\(B\) Within 30 days after October 10, 2000.

\(2\) For airplanes on which the repetitive inspections required by
paragraph (a) of AD 99-04-19 have NOT been initiated prior to October
10, 2000: Inspect at the earlier of the times specified by paragraphs
(a)(2)(i) and (a)(2)(ii) of this AD.

\(i\) Prior to the accumulation of 500 total flight cycles.

\(ii\) Prior to the accumulation of 2,000 total flight hours, or within
30 days after October 10, 2000, whichever occurs later.

**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.\'\'

**Corrective Action**

\(b\) If any cracking is detected during any inspection required by
paragraph (a) of this AD, prior to further flight, accomplish all
applicable corrective actions specified by and in accordance with Boeing
Alert Service Bulletin 777-57A0034, Revision 2, dated November 19, 1998;
Revision 3, dated May 4, 2000; Revision 4, dated July 20, 2000; or
Revision 5, dated January 25, 2001. The corrective actions include stop
drilling and repairing the crack and performing detailed inspections,
slat adjustment checks, and replacement of the slats. Where the alert
service bulletin specifies to contact Boeing for appropriate action:
Prior to further flight, repair in accordance with a method approved by
the Manager, Seattle Aircraft Certification Office (ACO), FAA. For a
repair method to be approved by the Manager, Seattle ACO, as required by
this paragraph, the Manager\'s approval letter must specifically
reference this AD. After October 10, 2000, only Revision 4 or 5 of the
alert service bulletin may be used.

**Optional Modification**

\(c\) Accomplishment of the actions specified by paragraphs (c)(1) and
(c)(2) of this AD extends the repetitive inspection interval specified
by paragraph (a) of this AD to 8,000 flight cycles.

\(1\) Install a seal insert into the spanwise bulb seals for the slats
in accordance with Part 4 of Boeing Alert Service Bulletin 777-57A0034,
Revision 3, dated May 4, 2000; Revision 4, dated July 20, 2000; or
Revision 5, dated January 25, 2001.

\(2\) Within 750 days or 4,000 flight cycles, whichever occurs first,
after installing the seal insert as specified by paragraph (c)(1) of
this AD: Perform a detailed inspection of the interior structure of the
cove skin at slat numbers 1 through 6 inclusive, and 9 through 14
inclusive, in accordance with Part 2 of the Accomplishment Instructions
of the alert service bulletin.

**New Requirements of This AD**

**Repetitive Inspections (Certain Airplanes)**

\(d\) For airplanes having line numbers 1 and 266 and subsequent: Prior
to the accumulation of 8,000 total flight cycles, or within 500 flight
cycles after the effective date of this AD, whichever occurs later,
perform a detailed inspection to detect cracking of the cove skin on the
outboard leading edge slats of the left and right wings at slat numbers
1 through 6 inclusive, and 9 through 14 inclusive; in accordance with
Boeing Alert Service Bulletin 777-57A0034, Revision 5, dated January 25,
2001. Repeat the inspection thereafter at intervals not to exceed 8,000
flight cycles.

**Corrective Action**

\(e\) If any cracking is detected during any inspection required by
paragraph (d) of this AD, prior to further flight, accomplish all
applicable corrective actions specified by and in accordance with Boeing
Alert Service Bulletin 777-57A0034, Revision 5, dated January 25, 2001.
The corrective actions include stop drilling and repairing the crack and
performing detailed inspections, slat adjustment checks, and replacement
of the slats. Where the alert service bulletin specifies to contact
Boeing for appropriate action: Prior to further flight, repair in
accordance with a method approved by the Manager, Seattle ACO. For a
repair method to be approved by the Manager, Seattle ACO, as required by
this paragraph, the Manager\'s approval letter must specifically
reference this AD.

**One-Time Inspection--Undersized Seal Inserts**

\(f\) For airplanes on which the optional modification described in
paragraph (c) of this AD was accomplished prior to the effective date of
this AD, in accordance with Part 4 of Boeing Alert Service Bulletin
777-57A0034, Revision 3, dated May 4, 2000; or Revision 4, dated July
20, 2000, using kits shipped before October 6, 2000: Within 500 flight
cycles after the effective date of this AD, do a one-time detailed
inspection for undersized seal inserts installed in the spanwise bulb
seals of slat numbers 4, 5, 10, and 11, in accordance with Part 5 of
Boeing Alert Service Bulletin 777-57A0034, Revision 5, dated January 25,
2001.

**Note 3:** An inspection accomplished prior to the effective date of
this AD in accordance with Boeing Telegraphic Message M-7200-00-02516,
\"Incorrect Insert Part Numbers in SB 777‑57A0034,\'\' dated October 13,
2000, is considered acceptable for compliance with paragraph (f) of this
AD.

\(1\) For any seal insert of the correct size as specified in Revision 5
of the service bulletin: No further action is required by this
paragraph.

\(2\) For any undersized seal insert as specified in Revision 5 of the
service bulletin, or for any seal insert that cannot be conclusively
determined to be of correct size: Prior to further flight, replace the
existing seal assembly with a new seal assembly, in accordance with
Revision 5 of the service bulletin.

**Spares**

\(g\) As of the effective date of this AD, no one may install a seal
insert into the spanwise bulb seals of slat numbers 4, 5, 10, and 11,
unless it is inspected in accordance with Part 4 of Boeing Alert Service
Bulletin 777-57A0034, Revision 5, dated January 25, 2001, and found to
be of correct size.

**Alternative Methods of Compliance**

(h)(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 ACO. 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 99-04-19, amendment 39-11044, are approved as
alternative methods of compliance with paragraph (b) of this AD.

**Special Flight Permits**

\(i\) 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**

\(j\) Except as provided by paragraphs (b) and (e) of this AD: The
actions shall be done in accordance with Boeing Alert Service Bulletin
777-57A0034, Revision 2, dated November 19, 1998; Boeing Alert Service
Bulletin 777-57A0034, Revision 3, dated May 4, 2000; Boeing Alert
Service Bulletin 777-57A0034, Revision 4, dated July 20, 2000; or Boeing
Alert Service Bulletin 777-57A0034, Revision 5, dated January 25, 2001;
as applicable.

\(1\) The incorporation by reference of Boeing Alert Service Bulletin
777-57A0034, Revision 5, dated January 25, 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 Boeing Alert Service Bulletin
777-57A0034, Revision 3, dated May 4, 2000; and Boeing Alert Service
Bulletin 777-57A0034, Revision 4, dated July 20, 2000; was approved
previously by the Director of the Federal Register as of October 10,
2000 (65 FR 57282, September 22, 2000).

\(3\) The incorporation by reference of Boeing Alert Service Bulletin
777-57A0034, Revision 2, dated November 19, 1998, was approved
previously by the Director of the Federal Register as of March 8, 1999
(64 FR 8230, February 19, 1999).

\(4\) 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**

\(k\) This amendment becomes effective on July 10, 2002.

**FOR FURTHER INFORMATION CONTACT:** Suzanne Masterson, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 227-2772; fax (425) 227-1181.

Issued in Renton, Washington, on May 23, 2002.

Ali Bahrami,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-13608 Filed 6-4-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**ROLLS-ROYCE PLC**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**LARGE AIRCRAFT**

**2002-11-08 Rolls-Royce plc:** Amendment 39-12769. Docket No.
2001-NE-17-AD.

**Applicability**

This airworthiness directive (AD) is applicable to Rolls-Royce plc. (RR)
RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines
with low pressure compressor (LPC) fan blades, part numbers (P/N\'s)
FK30838, FK30840, FK30842, FW12960, FW12961, FW12962, and FW13175,
installed. These engines are installed on, but not limited to, Boeing
Company 777 series airplanes.

**Note 1:** This AD applies to each engine identified in the preceding
applicability provision, regardless of whether it has been modified,
altered, or repaired in the area subject to the requirements of this AD.
For engines that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (h) 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 multiple LPC fan blade failures due to cracks, which could
result in uncontained engine failure and possible damage to the
airplane, do the following:

\(a\) Ultrasonic-inspect and disposition the dovetail roots of LPC fan
blades, P/N\'s FK30838, FK30840, FK30842, FW12960, FW12961, FW12962, and
FW13175, that are removed from the engine, in accordance with 3.A.(1)
through 3.A.(5) or, for blades that are not removed from the engine, in
accordance with 3.B.(1) through 3.B.(5) of the Accomplishment
Instructions of RR service bulletin (SB) RB.211-72-D344, Revision 4,
dated March 15, 2002.

\(b\) For blades P/N\'s FK30838, FK30840, and FK30842, that have not
been relubricated using either RR SB RB.211-72-D344 or RB.211-72-D347,
during any interval exceeding 600 cycles-since-new (CSN) or
cycles-since-rework (CSR), inspect in accordance with paragraph (a) of
this AD and within the compliance times specified in the following Table
1:

+-------------+-----------+----------------+---------+-----------------+
| > **TABLE   |           |                |         |                 |
| > 1**       |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > **Engine  | >         | > **Airplane   | > **    | > **Repetitive  |
| > series**  |  **Boeing | > maximum      | Initial | > inspection    |
|             | > 777     | > gross weight | > ins   | >               |
|             | > series  | > (times 1000  | pection |  (cycles-since- |
|             | > (IGW)** | > pounds)**    | >       | last-inspection |
|             |           |                | (CSN)** | > (CSLI)**      |
+-------------+-----------+----------------+---------+-----------------+
| > \(1\)     | > -300    | > \(i\) 660    | > 600   | > 80            |
| > -892      |           | > and 632.5    | >       | >               |
|             |           | >              | > 2,000 | > 600           |
|             |           | > \(ii\) 580   |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(2\)     | > -200    | > \(i\) 632.5  | > 1,200 | > 100           |
| > -884,     | > with    | > and 648      | >       | >               |
| > -892,     | > IGW     | >              | > 600   | > 80            |
| > ‑892B,    |           | > \(ii\) 656   | >       | >               |
| > and -895  |           | >              | > 2,000 | > 600           |
|             |           | > \(iii\) 555  |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(3\)     | > -200    | > 535          | > 2,000 | > 600           |
| > -875      |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(4\)     | > -200    | > 545          | > 2,000 | > 600           |
| > -877      |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+

\(c\) For blades P/N\'s FK30838, FK30840, and FK30842, that have been
relubricated at intervals not exceeding 600 CSN or CSR using either RR
SB RB.211-72-D344 or SB RB.211-72-D347, inspect in accordance with
paragraph (a) of this AD and within the compliance times specified in
the following Table 2:

+-------------+-----------+----------------+---------+-----------------+
| > **TABLE   |           |                |         |                 |
| > 2**       |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > **Engine  | >         | > **Airplane   | > **    | > **Repetitive  |
| > series**  |  **Boeing | > maximum      | Initial | > inspection    |
|             | > 777     | > gross weight | > ins   | >               |
|             | > series  | > (times 1000  | pection |  (cycles-since- |
|             | > (IGW)** | > pounds)**    | >       | last-inspection |
|             |           |                | (CSN)** | > (CSLI)**      |
+-------------+-----------+----------------+---------+-----------------+
| > \(1\)     | > -300    | > \(i\) 660    | > 600   | > 80            |
| > -892      |           | > and 632.5    | >       | >               |
|             |           | >              | > 2,400 | > 600           |
|             |           | > \(ii\) 580   |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(2\)     | > -200    | > \(i\) 632.5  | > 2,400 | > 100           |
| > -884,     | > with    | > and 648      | >       | >               |
| > -892,     | > IGW     | >              | > 600   | > 80            |
| > ‑892B,    |           | > \(ii\) 656   | >       | >               |
| > and -895  |           | >              | > 2,400 | > 600           |
|             |           | > \(iii\) 555  |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(3\)     | > -200    | > 535          | > 2,400 | > 600           |
| > -875      |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(4\)     | > -200    | > 545          | > 2,400 | > 600           |
| > -877      |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+

\(d\) For blades P/N\'s FW12960, FW12961, FW12962, and FW13175, either
new or reworked to that configuration at greater than 600 CSN or since
previous rework, or that have not been relubricated during any interval
exceeding 600 CSN or CSR using either RR SB RB.211-72-D344 or
RB.211-72-D347 requirements, inspect in accordance with paragraph (a) of
this AD and within the compliance times specified in the following Table
3:

+-------------+-----------+----------------+---------+-----------------+
| > **TABLE   |           |                |         |                 |
| > 3**       |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > **Engine  | >         | > **Airplane   | > **    | > **Repetitive  |
| > series**  |  **Boeing | > maximum      | Initial | > inspection    |
|             | > 777     | > gross weight | > ins   | > (CSLI)**      |
|             | > series  | > (times 1000  | pection |                 |
|             | > (IGW)** | > pounds)**    | >       |                 |
|             |           |                | (CSN)** |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(1\)     | > -300    | > \(i\) 660    | > 600   | > 100           |
| > -892      |           | > and 632.5    | >       | >               |
|             |           | >              | > 2,000 | > 600           |
|             |           | > \(ii\) 580   |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(2\)     | > -200    | > \(i\) 632.5  | > 1,200 | > 125           |
| > -884,     | > with    | > and 648      | >       | >               |
| > -892,     | > IGW     | >              | > 600   | > 100           |
| > ‑892B,    |           | > \(ii\) 656   | >       | >               |
| > and -895  |           | >              | > 2,000 | > 600           |
|             |           | > \(iii\) 555  |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(3\)     | > -200    | > 535          | > 2,000 | > 600           |
| > -875      |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(4\)     | > -200    | > 545          | > 2,000 | > 600           |
| > -877      |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+

\(e\) For blades P/N\'s FW12960, FW12961, FW12962, and FW13175, either
new or reworked to that configuration at fewer than 600 CSN or since
previous rework, and that have been relubricated using either RR SB
RB.211-72-D344 or SB RB.211-72-D347 at intervals not exceeding 600 CSN
or repetitive lubrication, inspect in accordance with paragraph (a) of
this AD and within the compliance times specified in the following Table
4:

+-------------+-----------+----------------+---------+-----------------+
| > **TABLE   |           |                |         |                 |
| > 4**       |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > **Engine  | >         | > **Airplane   | > **    | > **Repetitive  |
| > series**  |  **Boeing | > maximum      | Initial | > inspection**  |
|             | > 777     | > gross weight | > ins   | >               |
|             | > series  | > (times 1000  | pection | > **(CSLI)**    |
|             | > (IGW)** | > pounds)**    | >       |                 |
|             |           |                | (CSN)** |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(1\)     | > -300    | > \(i\) 660    | > 600   | > 100           |
| > -892      |           | > and 632.5    | >       | >               |
|             |           | >              | > 2,400 | > 1,200         |
|             |           | > \(ii\) 580   |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(2\)     | > -200    | > \(i\) 632.5  | > 2,400 | > 125           |
| > -884,     | > with    | > and 648      | >       | >               |
| > -892,     | > IGW     | >              | > 600   | > 100           |
| > ‑892B,    |           | > \(ii\) 656   | >       | >               |
| > and -895  |           | >              | > 2,400 | > 1,200         |
|             |           | > \(iii\) 555  |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(3\)     | > -200    | > 535          | > 2,400 | > 1,200         |
| > -875      |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+
| > \(4\)     | > -200    | > 545          | > 2,400 | > 1,200         |
| > -877      |           |                |         |                 |
+-------------+-----------+----------------+---------+-----------------+

\(f\) When engines containing blades P/N\'s FK30838, FK30840, FK30842,
FW12960, FW12961, FW12962, and FW13175 are moved from one gross weight
category to another, the inspection schedule that is applicable to the
higher gross weight category must be used.

**Optional Terminating Action**

\(g\) Replacement of LPC fan blades P/N\'s FK30838, FK30840, FK30842,
FW12960, FW12961, FW12962, and FW13175 with a complete set of LPC fan
blades that have a P/N that is not listed in this AD constitutes
terminating action for the repetitive inspection requirements of
paragraphs (a) through (e) of this AD.

**Alternative Methods of Compliance**

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

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

**Special Flight Permits**

\(i\) 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.

**Documents That Have Been Incorporated By Reference**

\(j\) The inspection must be done in accordance with Rolls-Royce plc.
(RR) service bulletin RB.211-72-D344, Revision 4, dated March 15, 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 Rolls-Royce plc P.O. Box 31, Derby DE24 6BJ,
UK; Telephone 44 (0) 1332 242424; fax 44 (0) 1332 249936. Copies may be
inspected, by appointment, at the FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive Park, Burlington, MA; or at
the Office of the Federal Register, 800 North Capitol Street, NW, suite
700, Washington, DC.

**Note 3:** The subject of this AD is addressed in CAA airworthiness
directive 001-02-2001, dated February 2, 2000.

**Effective Date**

\(k\) This amendment becomes effective on June 21, 2002.

**FOR FURTHER INFORMATION CONTACT:** Keith Mead, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7744; fax (781) 238-7199.

Issued in Burlington, Massachusetts, on May 27, 2002.

Mark C. Fulmer,

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

\[FR Doc. 02-13885 Filed 6-5-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**BOEING**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-11-11 Boeing:** Amendment 39-12772. Docket 2002-NM-133-AD.

**Applicability:** Model 767-200, -300, and -300F series airplanes with
non-fully-enclosed cargo floors in the lower cargo areas; certificated
in any category. A fully enclosed cargo floor is a floor with panels
installed between all roller trays in the cargo compartment. A
non-fully-enclosed cargo floor is a floor without panels installed
between all roller trays in the cargo compartment.

**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) 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 fire in the airplane due to overheating of heater tape on
potable water lines and drain lines, which may ignite combustible debris
or contaminants which have accumulated on or near the potable water and
drain lines, accomplish the following:

**Compliance Time**

\(a\) Within 18 months after date of delivery of the airplane, or within
90 days after the effective date of this AD, whichever occurs later:
Accomplish paragraphs (b) and (c) of this AD.

**Removal of Debris**

\(b\) Perform a one-time general visual inspection for foreign object
debris (FOD) or contamination in visually accessible areas on or near
potable water and drain lines located below the cargo floor in the
forward and aft cargo compartments, in accordance with Boeing Alert
Service Bulletin 767-30A0037, dated May 28, 2002. If FOD or
contamination is observed on or near the potable water or drain lines,
prior to further flight, remove it in accordance with the service
bulletin.

**Note 2:** The visual inspection of potable water and drain lines in
visually accessible areas does not require removal of floor panels.

**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.\'\'

**Inspection of Potable Water and Drain Lines**

\(c\) As indicated in paragraphs (c)(1) and (c)(2) of this AD, perform a
general visual inspection of visually accessible areas for discrepancies
of potable water and drain lines located below the cargo floor in the
forward and aft cargo compartments, in accordance with Boeing Alert
Service Bulletin 767-30A0037, dated May 28, 2002.

\(1\) Inspect potable water and drain lines for indications of
overheating of the heater tape, such as localized darkening of foam
insulation or protective tape. If such an indication of overheating is
observed, prior to further flight, replace the defective heater tape in
accordance with the service bulletin, removing floor panels as necessary
to replace the defective heater tape.

\(2\) Inspect potable water and drain lines for missing or damaged
protective tape and exposed foam insulation. If exposed foam insulation
is observed, prior to further flight, cover the foam insulation with a
continuous wrap of protective tape, in accordance with the service
bulletin. If protective tape is observed to be missing or damaged, prior
to further flight, replace the protective tape in accessible areas in
accordance with the service bulletin. It is not necessary to remove
floor panels to replace the protective tape.

**Alternative Methods of Compliance**

\(d\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, 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 4:** 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**

\(e\) 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**

\(f\) The actions shall be done in accordance with Boeing Alert Service
Bulletin 767-30A0037, dated May 28, 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**

\(g\) This amendment becomes effective on June 24, 2002.

**FOR FURTHER INFORMATION CONTACT:** Donald Eiford, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2788; fax (425) 227-1181.

Issued in Renton, Washington, on May 29, 2002.

Vi L. Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02-14129 Filed 6-6-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**BAE SYSTEMS (OPERATIONS)**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-12-01 BAE Systems (Operations) Limited (Formerly British
Aerospace Regional Aircraft):** Amendment 39-12773. Docket
2001-NM-151-AD.

**Applicability:** Model Jetstream 4101 airplanes, as listed in BAE
Systems (Operations) Limited (Jetstream) Service Bulletin J41-32-075,
dated April 18, 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 damage to the capsule in the upper and lower bearings of the
shortening mechanism of the nose landing gear, which could result in
inability to extend the nose landing gear in normal or emergency
situations, and consequent injury to passengers and flight crew,
accomplish the following:

**Functional Test/Corrective Action**

\(a\) Within 300 flight hours or 60 days after the effective date of
this AD, whichever comes first: Do a functional test of the shortening
mechanism of the nose landing gear for free movement of the capsule in
the upper and lower bearings, according to APPH Precision Hydraulics
Service Bulletin AIR83586-32-16, dated February 2001. If the capsule
does not move freely, before further flight, do the actions specified in
paragraph (a)(1) or (a)(2) of this AD, as applicable. If the capsule
moves freely, no further action is required by this paragraph.

\(1\) Rework according to APPH Precision Hydraulics Service Bulletin
AIR83586-32-16, dated February 2001.

\(2\) If the rework is not done, before further flight, do a full
functional test of the extension/retraction system of the nose landing
gear according to BAE Systems (Operations) Limited (Jetstream) Service
Bulletin J41-32-075, dated April 18, 2001, or Revision 1, dated May 18,
2001; and do the actions specified in paragraph (a)(1)(i) or (a)(2)(ii)
of this AD, as applicable.

\(i\) If the nose landing gear extends and retracts correctly, repeat
the full functional test every 50 flight hours according to the service
bulletin. Within 300 flight hours after the initial test, do the
requirements in paragraph (a)(1) of this AD, which ends the repetitive
testing specified in this paragraph.

\(ii\) If the nose landing gear does not extend and retract correctly,
before further flight, replace the nose landing gear with new landing
gear according to 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, International Branch, ANM-116, Transport
Airplane Directorate, FAA. 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 2:** 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**

\(c\) 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 APPH Precision
Hydraulics Service Bulletin AIR83586-32-16, dated February 2001; and BAE
Systems (Operations) Limited (Jetstream) Service Bulletin J41-32-075,
dated April 18, 2001; or BAE Systems (Operations) Limited (Jetstream)
Service Bulletin J41-32-075, Revision 1, dated May 18, 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 British Aerospace Regional Aircraft American
Support, 13850 Mclearen Road, Herndon, Virginia 20171. 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 16, 2002.

**FOR FURTHER INFORMATION CONTACT:** Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.

Issued in Renton, Washington, on June 3, 2002.

Ali Bahrami,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-14410 Filed 6-10-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**BOEING**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-12-05 Boeing:** Amendment 39-12777. Docket 2000-NM-382-AD.

**Applicability:** Model 767 series airplanes, line numbers 1 through
62; 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) 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 broken rivets in the nose wheel well side panels
and top panel, which could impair the function of the nose landing gear
and cause fatigue cracks in the nose wheel well side panel and top panel
webs, which could result in rapid cabin depressurization during flight,
accomplish the following:

**Initial and Repetitive Inspections**

\(a\) Within 18 months or 3,000 flight cycles after the effective date
of this AD, whichever occurs first: Perform a detailed inspection of the
nose wheel well side panels for broken rivets, in accordance with Boeing
Service Bulletin 767-53A0090, Revision 1, dated September 14, 2000.

**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:** Inspections, replacement, and repairs performed prior to the
effective date of this AD in accordance with Boeing Service Bulletin
767-53A0090, dated August 3, 2000, are considered acceptable for
compliance with the applicable actions specified in this amendment.

\(1\) If no broken rivets are detected: No further action is required as
part of the initial inspection. Repeat the inspection at intervals not
to exceed 18 months or 3,000 flight cycles, whichever occurs first.

\(2\) If broken rivets are detected, but they do not include two or more
adjacent rivets: Prior to further flight, replace the broken rivets with
bolts in accordance with the service bulletin. Repeat the inspection at
intervals not to exceed 18 months or 3,000 flight cycles, whichever
occurs first.

\(3\) If two or more adjacent broken rivets are detected: Prior to
further flight, perform a secondary inspection as specified in paragraph
(c) of this AD.

**Optional Terminating Action**

\(b\) Replacement of all the rivets with bolts in accordance with Figure
5 of Boeing Service Bulletin 767-53A0090, Revision 1, dated September
14, 2000, terminates the repetitive inspection required by paragraph (a)
of this AD.

**Secondary Inspections**

\(c\) If two or more adjacent broken rivets are found during any
inspection required by paragraph (a) of this AD: Prior to further
flight, perform a detailed inspection of the side panels and the top
panel of the nose wheel well for cracks or broken rivets, in accordance
with Boeing Service Bulletin 767-53A0090, Revision 1, dated September
14, 2000.

\(1\) If no cracks or additional broken rivets are found: Prior to
further flight replace all of the rivets with bolts in accordance with
Figure 5 of the service bulletin. This terminates the repetitive
inspections required by paragraph (a) of this AD.

\(2\) If any cracks or additional broken rivets are found: Prior to
further flight, repair the cracks and replace all of the rivets, per a
method approved by the Manager, Seattle Aircraft Certification Office,
or per data meeting the type certification basis of the airplane
approved by a Boeing Company Designated Engineering Representative who
has been authorized by the Manager, Seattle ACO, to make such findings.
For a repair method to be approved, the approval must specifically
reference this AD. This terminates the repetitive inspections required
by paragraph (a) of this AD.

**Alternative Methods of Compliance**

\(d\) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be used
if approved by the Manager, Seattle ACO. 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 4:** 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**

\(e\) 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**

\(f\) Except as provided by paragraph (c)(2) of this AD, the actions
required by paragraphs (a) and (c) of this AD shall be done in
accordance with Boeing Service Bulletin 767-53A0090, Revision 1, dated
September 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 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**

\(g\) This amendment becomes effective on July 18, 2002.

**FOR FURTHER INFORMATION CONTACT:** Suzanne Masterson, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 227-2772; fax (425) 227-1181.

Issued in Renton, Washington, on June 4, 2002.

Ali Bahrami,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-14584 Filed 6-12-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-12**

**PRATT & WHITNEY**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**LARGE AIRCRAFT**

**2002-12-06 Pratt & Whitney:** Amendment 39--12778. Docket No.
98-ANE-61-AD. Supersedes AD 2000-21-09, Amendment 39-11941

**Applicability**

This airworthiness directive (AD) is applicable to Pratt & Whitney (PW)
PW2037, PW2040, PW2037M, PW2240, PW2337, PW2043, PW2643, and PW2143,
series turbofan engines. These engines are installed on, but not limited
to Boeing 757 series and Ilyushin IL--96T series airplanes.

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

**Compliance**

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

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

\(a\) Within 30 days after the effective date of this AD, revise the
manufacturer\'s Time Limits section (TLS) of the manufacturer\'s engine
manual, as appropriate for PW PW2037, PW2040, PW2037M, PW2240, PW2337,
PW2043, PW2643, and PW2143 series turbofan engines, and for air carriers
revise the approved continuous airworthiness maintenance program, by
adding the following:

**Mandatory Inspections**

\(1\) Perform inspections of the following parts at each piece-part
opportunity in accordance with the instructions provided in PW2000
Engine Manuals 1A6231 and 1B2412:

+-------------------+------+----------+--------------------+----------+
| >                 | > ** | > **EM   | > **               | > **S    |
|  **Nomenclature** | Part | > manual | Inspection/check** | ubtask** |
|                   | > N  | > s      |                    |          |
|                   | o.** | ection** |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Hub, LPC        | >    | > 72     | > -06              |          |
| > Assembly        |  ALL | --31--04 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, HPT 1st   | >    | > 72     | > FPI entire disk  | > 72--   |
| > Stage           |  ALL | --52--02 | > per 72--52--00,  | 52--02-- |
|                   |      |          | > I                | 230--007 |
|                   |      |          | nspection/Check-02 |          |
+-------------------+------+----------+--------------------+----------+
| > Hub, HPT 2nd    | >    | > 72     | > FPI entire hub   | > 72--   |
| > Stage           |  ALL | --52--16 | > per 72--52-00,   | 52--16-- |
|                   |      |          | > I                | 230--007 |
|                   |      |          | nspection/Check-02 |          |
+-------------------+------+----------+--------------------+----------+
| > Hub, HPC Front  | >    | > 72     | > -05              |          |
|                   |  ALL | --35--02 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, HPC Drum  | >    | > 72     | > -04              |          |
| > Rotor Assembly  |  ALL | --35--03 |                    |          |
| > (7--15)         |      |          |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, HPC Drum  | >    | > 72     | > -05              |          |
| > Rotor Assembly  |  ALL | --35--10 |                    |          |
| > (16--17)        |      |          |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, HPC 16th  | >    | > 72     | > -04              |          |
| > Stage           |  ALL | --35--06 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, HPC 17th  | >    | > 72     | > -04              |          |
| > Stage           |  ALL | --35--07 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > HPC Turbine     | >    | > 72     | > -05              |          |
| > Drive Shaft     |  ALL | --35--08 |                    |          |
| > Assembly        |      |          |                    |          |
+-------------------+------+----------+--------------------+----------+
| > LPC Drive       | >    | > 72     | > -06              |          |
| > Turbine Shaft   |  ALL | --32--01 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Hub, Turbine    | >    | > 72     | > -06              |          |
| > Rear            |  ALL | --53--81 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, LPT 3rd   | >    | > 72     | > -01              |          |
| > stage           |  ALL | --53--31 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, LPT 4th   | >    | > 72     | > -01              |          |
| > Stage           |  ALL | --53--41 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, LPT 5th   | >    | > 72     | > -01              |          |
| > Stage           |  ALL | --53--51 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, LPT 6th   | >    | > 72     | > -01              |          |
| > Stage           |  ALL | --53--61 |                    |          |
+-------------------+------+----------+--------------------+----------+
| > Disk, LPT 7th   | >    | > 72     | > -01              |          |
| > Stage           |  ALL | --53--71 |                    |          |
+-------------------+------+----------+--------------------+----------+

\(2\) For the purposes of these mandatory inspections, piece-part
opportunity means:

\(i\) The part is considered completely disassembled when done in
accordance with the disassembly instructions in the manufacturer\'s
engine manual to either part number level listed in the table above, and

\(ii\) The part has accumulated more than 100 cycles in service since
the last piece-part opportunity inspection, provided that the part was
not damaged or related to the cause for its removal from the engine."

\(b\) Except as provided in paragraph (c) of this AD, and
notwithstanding contrary provisions in § 43.16 of Federal Aviation
Regulations (14 CFR 43.16), these enhanced inspections must be performed
only in accordance with the TLS of the appropriate PW2000 series engine
manuals.

**Alternative Methods of Compliance**

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

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

**Special Flight Permits**

\(d\) Special flight permits may be issued in accordance with §§ 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 § 121.369 (c) of the Federal Aviation Regulations (14 CFR
121.369 (c)) of this chapter must maintain records of the mandatory
inspections that result from revising the Time Limits section of the
Instructions for Continuous Airworthiness (ICA) 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 § 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 § 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.

**Effective Date**

\(f\) This amendment becomes effective on July 17, 2002.

**FOR FURTHER INFORMATION CONTACT:** Jason Yang, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803--5299; telephone (781)
238--7747; fax (781) 238--7199.

Issued in Burlington, Massachusetts, on June 4, 2002.

Francis A. Favara,

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

\[FR Doc. 02--14695 Filed 6--11--02; 8:45 am\]

BILLING CODE 4910--13--P

**BW 2002-12**

**HONEYWELL INTERNATIONAL, INC.**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**LARGE AIRCRAFT**

**2002--12--08 Honeywell International, Inc.:** Amendment 39--12780.
Docket No. 99--NE--51--AD.

**Applicability**

This airworthiness directive (AD) is applicable to Honeywell
International, Inc. (formerly AlliedSignal Inc., and Textron Lycoming)
ALF502 and LF507 series turbofan engines with certain first turbine
rotor sealing plates, first turbine rotor discs, and turbine spacers
installed. These engines are installed on, but not limited to,
Bombardier (Canadair) CL600--1A11, and British Aerospace BAe 146 series
and AVRO 146-RJ series airplanes.

**Note 1:** This AD applies to each engine identified in the preceding
applicability provision, regardless of whether it has been modified,
altered, or repaired in the area subject to the requirements of this AD.
For engines that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (f) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD; and,
if 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 gas producer turbine (GPT) component failure, which could
result in an uncontained engine failure and damage to the airplane, do
the following:

**Drawdown Schedule for First Turbine Rotor Sealing Plate**

\(a\) Remove from service first turbine rotor sealing plates according
to the drawdown plan described in the following Table 1 of this AD, and
replace with serviceable parts:

+------------+-------------------+-------------------------------------+
| > **TABLE  |                   |                                     |
| >          |                   |                                     |
| 1.---FIRST |                   |                                     |
| > TURBINE  |                   |                                     |
| > ROTOR    |                   |                                     |
| > SEALING  |                   |                                     |
| > PLATE**  |                   |                                     |
| >          |                   |                                     |
| > **Part   |                   |                                     |
| > Numbers  |                   |                                     |
| > (P/N's)  |                   |                                     |
| > 2--121   |                   |                                     |
| --075--15, |                   |                                     |
| > --21,    |                   |                                     |
| > --27,    |                   |                                     |
| > --28,    |                   |                                     |
| > and      |                   |                                     |
| > --36**   |                   |                                     |
+------------+-------------------+-------------------------------------+
| > **Engine | > **              | > **Replace**                       |
| > model**  | Cycles-in-service |                                     |
|            | > since new (CSN) |                                     |
|            | > on the          |                                     |
|            | > effective date  |                                     |
|            | > of this AD**    |                                     |
+------------+-------------------+-------------------------------------+
| > (        | > \(i\) Fewer     | > Before accumulating 20,000 CSN.   |
| 1)ALF502R, | > than 15,000 CSN | >                                   |
| >          | >                 | > Within 5,000 cycles-in-service    |
| LF507--1F, | > \(ii\) 15,000   | > (CIS) after the effective date of |
| > and      | > or more CSN     | > this AD or at the next access     |
| >          |                   | > after the effective date of this  |
| >          |                   | > AD, whichever is earlier, but do  |
|  LF507--1H |                   | > not exceed 25,000 CSN.            |
| > series   |                   |                                     |
+------------+-------------------+-------------------------------------+
| > \(2\)    | > \(i\) Fewer     | > Before accumulating 18,000 CSN.   |
| > All      | > than 17,500 CSN | >                                   |
| > ALF502L  | >                 | > Within 500 CIS after the          |
| > series   | > \(ii\) 17,500   | > effective date of this AD or at   |
|            | > or more CSN     | > the next access after the         |
|            |                   | > effective date of this AD,        |
|            |                   | > whichever is earlier, but do not  |
|            |                   | > exceed 23,000 CSN.                |
+------------+-------------------+-------------------------------------+

**Drawdown Schedule for First Turbine Rotor Disc**

\(b\) Remove from service first turbine rotor discs according to the
drawdown plan described in the following Table 2 of this AD, and replace
with serviceable parts:

+------------+-------------------+-------------------------------------+
| > **TABLE  |                   |                                     |
| >          |                   |                                     |
| 2.---FIRST |                   |                                     |
| > TURBINE  |                   |                                     |
| > ROTOR    |                   |                                     |
| > DISC**   |                   |                                     |
| >          |                   |                                     |
| > **P/N's  |                   |                                     |
| > 2--121   |                   |                                     |
| --051--18, |                   |                                     |
| > --24,    |                   |                                     |
| > --25,    |                   |                                     |
| > --R35,   |                   |                                     |
| > --36,    |                   |                                     |
| > --37,    |                   |                                     |
| > --44,    |                   |                                     |
| > --R52,   |                   |                                     |
| > and      |                   |                                     |
| > --R55**  |                   |                                     |
+------------+-------------------+-------------------------------------+
| > **Engine | > **              | > **Replace**                       |
| > model**  | Cycles-in-service |                                     |
|            | > since new (CSN) |                                     |
|            | > on the          |                                     |
|            | > effective date  |                                     |
|            | > of this AD**    |                                     |
+------------+-------------------+-------------------------------------+
| > \(1\)    | > \(i\) Fewer     | > Before accumulating 20,000 CSN.   |
| > ALF502R, | > than 15,000 CSN | >                                   |
| >          | >                 | > Within 5,000 CIS after the        |
| LF507--1F, | > \(ii\) 15,000   | > effective date of this AD or at   |
| > and      | > or more CSN     | > the next access after the         |
| >          |                   | > effective date of this AD,        |
|  LF507--1H |                   | > whichever is earlier, but do not  |
| > series   |                   | > exceed 25,000 CSN.                |
+------------+-------------------+-------------------------------------+
| > \(2\)    | > \(i\) Fewer     | > Before accumulating 14,000 CSN.   |
| > All      | > than 13,500 CSN | >                                   |
| > ALF502L  | >                 | > Within 500 CIS after the          |
| > series   | > \(ii\) 13,500   | > effective date of this AD or at   |
|            | > or more CSN     | > the next access after the         |
|            |                   | > effective date of this AD,        |
|            |                   | > whichever is earlier, but do not  |
|            |                   | > exceed 21,000 CSN.                |
+------------+-------------------+-------------------------------------+

**Drawdown Schedule for Turbine Spacer**

\(c\) Remove from service turbine spacers according to the drawdown plan
described in the following Table 3 of this AD, and replace with
serviceable parts:

+-----------------+---------------+--------------+--------------------+
| > **TABLE       |               |              |                    |
| > 3.---TURBINE  |               |              |                    |
| > SPACER**      |               |              |                    |
| >               |               |              |                    |
| > **P/N's       |               |              |                    |
| > 2             |               |              |                    |
| --121--071--36, |               |              |                    |
| > --37, and     |               |              |                    |
| > --42**        |               |              |                    |
+-----------------+---------------+--------------+--------------------+
| > **Engine      | > **First     | > **Cycle    | > **Replace**      |
| > model**       | > turbine     | s-in-service |                    |
|                 | > rotor       | > since new  |                    |
|                 | > assembly    | > (CSN) on   |                    |
|                 | > P/N**       | > the        |                    |
|                 |               | > effective  |                    |
|                 |               | > date of    |                    |
|                 |               | > this AD**  |                    |
+-----------------+---------------+--------------+--------------------+
| > \(1\) ALF502R | > P/N         | > \(i\)      | > Before           |
| > series        | > 2--         | > Fewer than | > accumulating     |
| > (except       | 121--090--63, | > 10,000 CSN | > 15,000 CSN.      |
| > ALF502R--3,   | > --64, --65, | >            | >                  |
| > see           | > --R66, or   | > \(ii\)     | > Within 5,000 CIS |
| > information   | > --R67.      | > 10,000 or  | > after the        |
| > in Note 2),   |               | > more CSN   | > effective date   |
| > LF507--1F,    |               |              | > of this AD or at |
| > and LF507--1H |               |              | > the next access  |
| > series        |               |              | > after the        |
|                 |               |              | > effective date   |
|                 |               |              | > of this AD,      |
|                 |               |              | > whichever is     |
|                 |               |              | > earlier, but do  |
|                 |               |              | > not exceed       |
|                 |               |              | > 20,000 CSN.      |
+-----------------+---------------+--------------+--------------------+
| > \(2\) ALF502R | > P/N         |              | > Before           |
| > series        | > 2-          |              | > accumulating     |
|                 | -121--090--41 |              | > 12,000 CSN.      |
|                 | > or --42 or  |              |                    |
|                 | > if rotor    |              |                    |
|                 | > assembly    |              |                    |
|                 | > P/N cannot  |              |                    |
|                 | > be          |              |                    |
|                 | > determined. |              |                    |
+-----------------+---------------+--------------+--------------------+
| > \(3\) All     | > P/N         | > \(i\)      | > Before           |
| > ALF502L       | > 2--         | > Fewer than | > accumulating     |
| > series        | 121--090--63, | > 13,500 CSN | > 14,000 CSN.      |
|                 | > --64, --65, | >            | >                  |
|                 | > --R66,      | > \(ii\)     | > Within 500 CIS   |
|                 | > --R67,      | > 13,500 or  | > after the        |
|                 | > --91,       | > more CSN   | > effective date   |
|                 | > --R92.      |              | > of this AD or at |
|                 |               |              | > the next access  |
|                 |               |              | > after the        |
|                 |               |              | > effective date   |
|                 |               |              | > of this AD,      |
|                 |               |              | > whichever is     |
|                 |               |              | > earlier, but do  |
|                 |               |              | > not exceed       |
|                 |               |              | > 19,500 CSN.      |
+-----------------+---------------+--------------+--------------------+
| > \(4\) All     | > P/N         |              | > Before           |
| > ALF502L       | > 2--         |              | > accumulating     |
| > series        | 121--090--41, |              | > 10,800 CSN.      |
|                 | > --42 or if  |              |                    |
|                 | > rotor       |              |                    |
|                 | > assembly    |              |                    |
|                 | > P/N cannot  |              |                    |
|                 | > be          |              |                    |
|                 | > determined. |              |                    |
+-----------------+---------------+--------------+--------------------+

**Note 2:** For ALF502R--3 engines, turbine spacers P/N\'s
2--121--071--37/-42 are not affected by this drawdown plan. Their life
limit remains at 11,600 CSN.

**Reduced Life Limits**

\(d\) Except for the drawdown provisions of paragraphs (a), (b), and (c)
of this AD and the approvals granted under the provisions of paragraph
(f) of this AD, no first turbine rotor sealing plates, first turbine
rotor discs, or turbine spacers may remain in service beyond the cyclic
life limits provided in paragraphs (a), (b), or (c) of this AD.

**Definitions**

\(e\) For the purposes of this AD, access is defined as when the engine
has been disassembled to where the affected part may be removed.

**Alternative Methods of Compliance**

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

**Note 3:** Information concerning the existence of approved alternative
methods of compliance with this airworthiness directive, if any, may be
obtained from the LAACO.

**Special Flight Permits**

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

**Effective Date**

\(h\) This amendment becomes effective on July 17, 2002.

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

Issued in Burlington, Massachusetts, on June 5, 2002.

Francis A. Favara,

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

\[FR Doc. 02--14697 Filed 6--11--02; 8:45 am\]

BILLING CODE 4910--13--P