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# **FEDERAL AVIATION ADMINISTRATION**

## **AIRWORTHINESS DIRECTIVES**

**LARGE AIRCRAFT**

**BIWEEKLY 2002-14**

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

U.S. Department of Transportation

### Federal Aviation Administration

Regulatory Support Division

Delegation and Airworthiness Programs Branch, AIR-140

P. O. Box 26460

Oklahoma City, OK 73125-0460

FAX 405-954-4104

Biweekly 2002-01

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

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

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

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

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

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

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

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

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

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

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

  2001-26-18              Dornier Luftfahrt 328-300 Series

  2001-26-19              Boeing            767 Series

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

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

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

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

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

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

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

Biweekly 2002-02

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

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

  2002-01-08              Israel Aircraft   Galaxy
                          Industries        

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

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

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

Biweekly 2002-03

+--------+---------+----------------+---------------------------------+
| 2001   | R1      | Raytheon       | DH.125, HS.125, BH.125, and     |
| -17-26 |         | Aircraft       | BAe.125 (U-125 and C-29A)       |
|        |         |                | Series, Hawker 800, Hawker 800  |
|        |         |                | (U-125A), Hawker 800XP, Hawker  |
|        |         |                | 1000                            |
+--------+---------+----------------+---------------------------------+
| 2001   | COR S   | McDonnell      | DC-9-10, -20, -30, -40, and -50 |
| -24-27 | 9       | Douglas        | Series; DC-9-81, -82, -83, and  |
|        | 6-02-05 |                | -87 Series,; MD-88; and C-9     |
|        |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2001   | COR     | Honeywell      | Engine: LTS101-600A-2 and       |
| -25-04 |         | International  | LTS101-600A-3 Turboshaft;       |
|        |         | Inc.           | LTP101-600A-1A and              |
|        |         |                | LTP101-700A-1A Turboprop        |
+--------+---------+----------------+---------------------------------+
| 2002   |         | General        | Engine: CF6-80E1                |
| -01-04 |         | Electric       |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Boeing         | 767 Series                      |
| -01-13 | 9       |                |                                 |
|        | 6-21-06 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Boeing         | 767-200, -300, and -300F Series |
| -01-15 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | Fairchild      | SA26-AT, SA226-AT, SA226-T,     |
| -01-16 | 8       | Aircraft       | SA226-T(B), SA226-TC, SA227-AC, |
|        | 6-24-11 |                | SA227-AT, SA227-TT              |
|        | &       |                |                                 |
|        |         |                |                                 |
|        | 8       |                |                                 |
|        | 6-25-04 |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Dornier        | 328-100 Series                  |
| -01-17 |         | Luftfahrt      |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Airbus         | A319, A320, and A321 Series     |
| -01-18 |         | Industrie      |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Fokker         | F.28 Mark 0070 and 0100 Series  |
| -01-19 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | BAE Systems    | BAe 146-200A Series             |
| -01-20 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | BAE Systems    | BAe-146 Series and Avro 146-RJ  |
| -01-21 |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Short Brothers | SD3 Series                      |
| -01-22 |         |                |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Raytheon       | Beech 400, Beech 400A, Beech    |
| -01-23 |         | Aircraft       | 400T Series, Beech 400T-1,      |
|        |         |                | Beech MU-300-10, Mitsubishi     |
|        |         |                | MU-300                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | McDonnell      | DC-9-81, -82, , -83, and -87    |
| -01-24 |         | Douglas        | Series, and MD-88               |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Bombardier     | DHC-8-100, -200, and -300       |
| -01-25 |         |                | Series                          |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Israel         | 1124 and 1124A Series, and 1125 |
| -01-26 |         | Aircraft       | Westwind Astra Series           |
+--------+---------+----------------+---------------------------------+
| 2002   | S       | General        | Engine: GE90-76B, -77B, -85B,   |
| -01-27 | 9       | Electric       | and -90B Turbofan               |
|        | 8-15-03 | Company        |                                 |
+--------+---------+----------------+---------------------------------+
| 2002   |         | Dowty          | Propeller: R334/4-82-F/13       |
| -01-28 |         | Aerospace      |                                 |
+--------+---------+----------------+---------------------------------+

Biweekly 2002-03 cont\'d...

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

  2002-02-02              Boeing            707 and 720 Series

  2002-02-03              BAE Systems       BAe 146 Series

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

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

Biweekly 2002-04

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

  2002-02-04                Boeing            757 Series

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

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

  2002-02-07                Airbus Industrie  A330 and A340 Series

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

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

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

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

  2002-03-05                McDonnell Douglas DC-8 Series

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

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

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

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

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

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

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

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

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

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

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

  2002-04-03                Fokker            F27 Mark 050 Series

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

Biweekly 2002-05

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

Biweekly 2002-06

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

Biweekly 2002-07

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

Biweekly 2002-08

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

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

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

  2002-07-07                Boeing            777-200 Series

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

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

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

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

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

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

  2002-08-02   S 2001-20-14 Fairchild         SA226-AT, SA226-T, SA226-T(B),
                            Aircraft          SA226-TC, SA227-AC, SA227-AT,
                                              SA227-TT, and SA227-TT(300)

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

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

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

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

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

Biweekly 2002-09

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

**Biweekly 2002-10**

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

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

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

  2002-10-02              Boeing            757 Series

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

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

**Biweekly 2002-11**

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

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

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

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

  2002-10-09              Gulfstream        Galaxy and Gulfstream 200
                          Aerospace         

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

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

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

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

**Biweekly 2002-12**

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

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

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

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

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

  2002-12-01                BAe Systems       Jetstream 4101

  2002-12-05                Boeing            767 Series

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

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

**Biweekly 2002-13**

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

**Biweekly 2002-14**

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

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

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

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

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

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

  2002-14-02                Boeing            767-300 series

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

**BW 2002-14**

**ROLLS-ROYCE, PLC.**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**LARGE AIRCRAFT**

**CORRECTION** *\[Federal Register: July 3, 2002 (Volume 67, Number
128); Page 44526-44527;*
*www.access.gpo.gov/su_docs/aces/aces140.html\]*

**2002-09-02 Rolls-Royce, plc.:** Amendment 39-12735. Docket No.
2001-NE-36-AD.

**Applicability**

This airworthiness directive (AD) is applicable to Rolls-Royce plc. Tay
Model 650-15 and 651-54 turbofan engines. These engines are installed
on, but not limited to Boeing 727 and Fokker 100 airplanes.

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

**Compliance**

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, accomplish the following:

\(a\) Within the next 30 days after the effective date of this AD,
revise the Airworthiness Limitations Section (ALS) and Maintenance
Scheduling Section (MSS) of the Instructions for Continued Airworthiness
(ICA) in the Time Limits Manuals publication number (P/N) T-TAY-3RR, and
T-TAY-5RR of the Engine Manuals, P/N E-TAY-3RR, and E-TAY-5RR as
applicable, and for air carrier operations revise the approved
continuous airworthiness maintenance program, by adding the following:
\"GROUP A PARTS MANDATORY INSPECTION TASK 05-20-01-200-001

\(1\) General: A full inspection of Group A Parts must be effected
whenever the following conditions are satisfied.

\(i\) When the component has been completely disassembled to piece-part
level in accordance with the appropriate disassembly procedures
contained in the Engine Manual. and

\(ii\) The part has accumulated in excess of 100 flight cycles in
service or since the last piece-part inspection. or

\(iii\) The component removal was for damage or a cause directly related
to its removal.

\(2\) Mandatory inspections for individual Group A Parts are specified
below: For time limits manual T-TAY-3RR and T-TAY-5RR (reference engine
manual E-TAY-3RR and E-TAY-5RR) only, insert the following Table:

+----------------------------------------+---------+------------------+
| > **Part nomenclature**                | >       | > **Inspected    |
|                                        |  **Part | > per overhaul   |
|                                        | > No.** | > manual task**  |
+----------------------------------------+---------+------------------+
| > Low Pressure Compressor Rotor Disc   | > All   | > 72--           |
|                                        |         | 31--11--200--000 |
+----------------------------------------+---------+------------------+
| > I. P. Compressor Rotor---Stage 1     | > All   | > 72--           |
| > Disc                                 |         | 33--31--200--000 |
+----------------------------------------+---------+------------------+
| > I. P. Compressor Rotor---Stage 2     | > All   | > 72--           |
| > Disc                                 |         | 33--32--200--000 |
+----------------------------------------+---------+------------------+
| > I. P. Compressor Rotor---Stage 3     | > All   | > 72--           |
| > Disk                                 |         | 33--33--200--000 |
+----------------------------------------+---------+------------------+
| > L. P. and I. P. Compressor Drive     | > All   | > 72--           |
| > Shaft                                |         | 33--40--200--000 |
+----------------------------------------+---------+------------------+
| > H. P. Compressor Rear Drive Shaft    | > All   | > 72--           |
|                                        |         | 37--31--200--000 |
+----------------------------------------+---------+------------------+
| > L. P. Compressor Rotor Drive Shaft   | > All   | > 72--           |
|                                        |         | 37--32--200--002 |
+----------------------------------------+---------+------------------+
| > H. P. Compressor Stage 1 Rotor Disc  | > All   | > 72--           |
|                                        |         | 37--33--200--001 |
+----------------------------------------+---------+------------------+
| > H. P. Compressor Stages 2 and 3      | > All   | > 72--           |
| > Rotor Discs                          |         | 37--33--200--002 |
+----------------------------------------+---------+------------------+
| > H. P. Compressor Stages 4, 5, 6, and | > All   | > 72--           |
| > 7 Rotor Discs                        |         | 37--34--200--000 |
+----------------------------------------+---------+------------------+
| > H. P. Compressor Stages 8, 9, 10,    | > All   | > 72--           |
| > and 11 Rotor Discs                   |         | 37--35--200--000 |
+----------------------------------------+---------+------------------+
| > H.P. Compressor Stage 10 to 11 Rotor | > All   | > 72--           |
| > Disc Spacer                          |         | 37--35--200--001 |
+----------------------------------------+---------+------------------+
| > H. P. Compressor Stage 12 Rotor Disc | > All   | > 72--           |
|                                        |         | 37--36--200--001 |
+----------------------------------------+---------+------------------+
| > H.P. Compressor Stage 11 to 12 Rotor | > All   | > 72--           |
| > Disc Spacer                          |         | 37--36--200--003 |
+----------------------------------------+---------+------------------+
| > H. P. Turbine Shaft                  | > All   | > 72--           |
|                                        |         | 41--31--200--000 |
+----------------------------------------+---------+------------------+
| > H. P. Stage 1 Rotor Disc             | > All   | > 72--           |
|                                        |         | 41--32--200--000 |
+----------------------------------------+---------+------------------+
| > H. P. Turbine Stage 2 Rotor Disc     | > All   | > 72--           |
|                                        |         | 41--33--200--000 |
+----------------------------------------+---------+------------------+
| > L. P. Turbine Shaft                  | > All   | > 72--           |
|                                        |         | 52--21--200--003 |
+----------------------------------------+---------+------------------+
| > L. P. Turbine Stage 1 Rotor Disc     | > All   | > 72--           |
|                                        |         | 52--22--200--000 |
+----------------------------------------+---------+------------------+
| > L. P. Turbine Stage 2 Rotor Disc     | > All   | > 72--           |
|                                        |         | 52--23--200--000 |
+----------------------------------------+---------+------------------+
| > L. P. Turbine Stage 3 Rotor Disc     | > All   | > 72--           |
|                                        |         | 52--24--200--000 |
+----------------------------------------+---------+------------------+

\(b\) Except as provided in paragraph (c) of this AD, and
notwithstanding contrary provisions in section 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these mandatory inspections must be
performed only in accordance with the TLM and applicable Engine Manual.

**Alternative Method of Compliance**

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

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

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

\(e\) The records of the mandatory inspections required as a result of
revising the TLM and the applicable Engine Manual and the air carrier\'s
continuous airworthiness maintenance program as provided by paragraph
(a) of this AD must be maintained by FAA-certificated air carriers which
have an approved continuous airworthiness maintenance program in
accordance with the record keeping system currently specified in their
manual required by sections 121.369 of the Federal Aviation Regulations
(14 CFR 121.369); or, in lieu of the record showing the current status
of each mandatory inspection required by sections 121.380(a)(2)(vi) of
the Federal Aviation Regulations (14 CFR 121.380(a)(2)(vi)),
certificated air carriers may establish an approved alternate 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
sections 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.

**Note 3:** The requirements of this AD have been met when the engine
shop manual changes are made and air carriers have modified their
continuous airworthiness maintenance plans to reflect the requirements
in the engine shop manuals.

**Effective Date**

\(f\) This amendment becomes effective on June 6, 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 April 23, 2002.

Marc J. Bouthillier,

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

\[FR Doc. 02-10549 Filed 5-1-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-14**

**GENERAL ELECTRIC COMPANY**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**LARGE AIRCRAFT**

\[Editorial Correction; Federal Register: July 8, 2002 (Volume 67,
Number 130); Page 45192 www.access.gpo.gov/su_docs/aces/aces140.html\]
to correct docket number. This copy reflects the correction*.*

**2002-10-08 General Electric Company:** Amendment 39-12754. **Docket
No. 2002-NE-04-AD**.

**Applicability**

This airworthiness directive (AD) is applicable to General Electric
Company (GE) CF6-80E1 series turbofan engines. These engines are
installed on, but not limited to, Airbus Industrie A330 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 (d) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD; and,
if the unsafe condition has not been eliminated, the request should
include specific proposed actions to address it.

**Compliance**

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

To prevent inadvertent in-flight thrust reverser deployment, which can
result in loss of control of the airplane, do the following:

**Engines That Do Not Have Improved Double P-Seal Configuration**

\(a\) For engines that do not have the improved double P-seal
configuration introduced by Middle River Aircraft Systems (MRAS) service
bulletin (SB) 78-5037, original issue or Revision 1, inspect and check
each fan thrust reverser half in accordance with 2.B., 2.C., and 2.D. of
the Accomplishment Instructions of MRAS alert service bulletin (ASB) No.
78A5043, Revision 1, dated January 22, 2002, as follows:

\(1\) Perform initial inspections and checks before exceeding 7,000
flight hours time-since-new (TSN) or 1,000 flight hours time-

in-service (TIS), whichever occurs later, after the effective date of
this AD.

\(2\) Thereafter, perform inspections and checks at intervals not to
exceed 7,000 flight hours TIS since last inspection or check.

**Engines That Do Have Improved Double P-Seal Configuration**

\(b\) For engines that do have the improved double P-seal configuration
introduced by MRAS SB 78-5037, original issue or Revision 1, inspect and
check each fan thrust reverser half in accordance

with 2.B. and 2.C. of the Accomplishment Instructions of MRAS ASB No.
78A5043, Revision 1, dated January 22, 2002, as follows:

\(1\) Perform initial inspections and checks before exceeding 25,000
flight hours TSN or 1,000 flight hours TIS, whichever occurs later,
after the effective date of this AD.

\(2\) Thereafter, perform inspections and checks at intervals not to
exceed 25,000 flight hours TIS since last inspection or check.

\(c\) Also for engines that do have the improved double P-seal
configuration introduced by MRAS SB 78-5037, original issue or Revision
1, check each fan thrust reverser half in accordance with 2D. of the
Accomplishment Instructions of MRAS ASB No. 78A5043, Revision 1, dated
January 22, 2002, as follows:

\(1\) Perform initial check before exceeding 7,000 flight hours TSN or
1,000 flight hours TIS, whichever occurs later, after the effective date
of this AD.

\(2\) Thereafter, perform checks at intervals not to exceed 7,000 flight
hours TIS since last check.

**Alternative Methods of Compliance**

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

**Note 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**

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

**Documents That Have Been Incorporated By Reference**

\(f\) The inspections and checks must be done in accordance with Middle
River Aircraft Systems Alert Service Bulletin No. CF6-80E1 SB 78A5043,
Revision 1, dated January 22, 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 Middle
River Aircraft Systems, Mail Point 46, 103 Chesapeake Park Plaza,
Baltimore, MD, 21220-4295, attn: Warranty Support, telephone: (410)
682-0094, fax: (410) 682-0100. Copies may be inspected, by appointment,
at the FAA, New England Region, Office of the Regional Counsel, 12 New
England Executive Park, Burlington, MA; or at the Office of the Federal
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

**Effective Date**

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

**FOR FURTHER INFORMATION CONTACT:** Karen Curtis, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Office Park; telephone (781) 238-7192; fax (781)
238-7199.

Issued in Burlington, Massachusetts, on May 9, 2002.

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

\[FR Doc. 02-12631 Filed 5-22-02; 8:45 am\]

BILLING CODE 4910-13-U

**BW 2002-14**

**HONEYWELL, INC.**

**AIRWORTHINESS DIRECTIVE**

**APPLIANCE**

**LARGE AIRCRAFT**

**2002-13-07 Honeywell, Inc.:** Amendment 39-12795; Docket No.
2001-CE-28-AD.

\(a\) *What aircraft are affected by this AD?* This AD affects any
aircraft, certificated in any category, that incorporates one of the
following:

\(1\) Inertial Reference Unit (IRU) part number (P/N) HG1075AB05, any
serial number (last four digits) 0644 through 0723 (excluding 0652 and
0659), that incorporates modification status 3. This AD does not apply
to these units if they incorporate modification status 7; or

\(2\) IRU P/N HG1075GB05, any serial number (last four digits) 0652 or
0659, that incorporates modification status 2. This AD does not apply to
these units if they incorporate modification status 6.

**Note 1:** These IRUs are primarily used on early manufactured Dassault
Falcon Jets, but could be incorporated on other aircraft through the
technical standard order (TSO) or supplemental type certificate (STC).

\(b\) *Who must comply with this AD?* Anyone who wishes to operate an
aircraft with any of the equipment identified in paragraph (a) of this
AD installed must comply with this AD.

\(c\) *What problem does this AD address?* The actions specified by this
AD are intended to ensure the correct transition of the IRU to battery
power upon the loss of primary power. Failure of an IRU to transition to
backup battery power could result in loss of attitude, heading, and
position reference and lead to the pilot making flight decisions that
put the aircraft in unsafe flight conditions.

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

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

  \(1\) Inspect any affected Within the next 50      In accordance with the
  IRU for proper function    hours time-in-service   instructions in
                             (TIS) after August 9,   Honeywell Alert
                             2002 (the effective     Service Bulletin
                             date of this AD).       HG1075AB--34--A0013,
                                                     dated May 21, 2001; or
                                                     Honeywell Alert
                                                     Service Bulletin
                                                     HG1075GB--34--A0005,
                                                     dated May 21, 2001, as
                                                     applicable.
  -------------------------- ----------------------- ----------------------

  -------------------------- ----------------------- ----------------------
  \(2\) Remove any affected  If found to not         In accordance with the
  IRU from the airplane.     function properly       instructions in
                             during the inspection   Honeywell Alert
                             required by paragraph   Service Bulletin
                             (d)(1) of this AD,      HG1075AB--34--A0013,
                             remove prior to further dated May 21, 2001; or
                             flight after the        Honeywell Alert
                             inspection. If found to Service Bulletin
                             function properly,      HG1075GB--34--A0005,
                             remove within 200 hours dated May 21, 2001, as
                             time-in-service (TIS)   applicable.
                             after the inspection    
                             required by paragraph   
                             (d)(1) of this AD..     

  \(3\) Do not install, on   As of August 9, 2002    Not Applicable.
  any aircraft, one of the   (the effective date of  
  IRU's identified in        this AD).               
  paragraphs (a)(1) and                              
  (a)(2) of this AD, unless                          
  it has been modified at                            
  Honeywell, Inc. and                                
  updated to one of the                              
  following:\                                        
  (i) IRU P/N HG1075AB05 IRU                         
  Mod 7; or\                                         
  (ii) IRU P/N HG1075GB05                            
  IRU Mod 6..                                        
  -------------------------- ----------------------- ----------------------

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

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

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

**Note 2:** This AD applies to each airplane identified in paragraph (a)
of this AD, regardless of whether it has been modified, altered, or
repaired in the area subject to the requirements of this AD. For
airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the owner/

operator must request approval for an alternative method of compliance
in accordance with paragraph (e) of this AD. The request should include
an assessment of the effect of the modification, alteration, or repair
on the unsafe condition addressed by this AD; and, if you have not
eliminated the unsafe condition, specific actions you propose to address
it.

\(f\) *Where can I get information about any already-approved
alternative methods of compliance?* Contact Wesley Rouse, Aerospace
Engineer, FAA, Chicago Aircraft Certification Office, 2300 E. Devon
Avenue, Des Plaines, Illinois 60018; telephone: (847) 294-8113;
facsimile: (847) 294-7834.

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

\(h\) *Are any service bulletins incorporated into this AD by
reference?* Actions required by this AD must be done in accordance with
Honeywell Alert Service Bulletin HG1075AB-34-A0013, dated May 21, 2001
or Honeywell Alert Service Bulletin HG1075GB-34-A0005, dated May 21,
2001, as applicable. The Director of the Federal Register approved this
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You
may get copies from Honeywell, Inc., Customer Response Center at
1-877-436-2005. You may view copies at the FAA, Central Region, Office
of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or
at the Office of the Federal Register, 800 North Capitol Street, NW,
suite 700, Washington, DC.

\(i\) *When does this amendment become effective?* This amendment
becomes effective on August 9, 2002.

**FOR FURTHER INFORMATION CONTACT:** Wesley Rouse, Aerospace Engineer,
FAA, Chicago Aircraft Certification Office, 2300 E. Devon Avenue, Des
Plaines, Illinois 60018; telephone: (847) 294-7564; facsimile: (847)
294-7834.

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

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft Certification Service.

\[FR Doc. 02-16307 Filed 6-28-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-14**

**PRATT & WHITNEY.**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**LARGE AIRCRAFT**

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

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

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

**Compliance:** Required as indicated, unless already done.

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

**Inspections**

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

\'\'Critical Life Limited Part Inspection

A. Inspection Requirements:

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

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

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

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

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

B. Parts Requiring Inspection.

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

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

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

  Hub (Disk), 1st Stage Compressor:                         

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

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

                                                            

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

                                                            

  HP Turbine, First Stage:                                  

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

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

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

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

  Disk, 4th Stage Turbine---.                 72--53--18    --02''
  ------------------------------------------- ------------- ---------------

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

**Alternative Methods of Compliance**

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

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

**Ferry Flights**

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

**Continuous Airworthiness Maintenance Program**

\(e\) FAA-certificated air carriers that have an approved continuous
airworthiness maintenance program in accordance with the record keeping
requirement of Sec. 121.369(c) of the Federal Aviation Regulations (14
CFR 121.369(c)) must maintain records of the mandatory inspections that
result from revising the TLS of the PW JT8D-200 Turbofan Engine Manual,
and the air carrier\'s continuous airworthiness program. Alternatively,
certificated air carriers may establish an approved system of record
retention that provides a method for preservation and retrieval of the
maintenance records that include the inspections resulting from this AD,
and include the policy and procedures for implementing this alternate
method in the air carrier\'s maintenance manual required by Sec.
121.369(c) of the Federal Aviation Regulations (14 CFR 121.369(c));
however, the alternate system must be accepted by the appropriate PMI
and require the maintenance records be maintained either

indefinitely or until the work is repeated. Records of the piece-part
inspections are not required under Sec. 121.380 (a)(2)(vi) of the
Federal Aviation Regulations (14 CFR 121.380(a)(2)(vi)). All other
operators must maintain the records of mandatory inspections required by
the applicable regulations governing their operations.

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

**Effective Date**

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

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

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

Jay J. Pardee,

Manager, Engine and Propeller Directorate, Aircraft Certification
Service.

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

BILLING CODE 4910-13-P

**BW 2002-14**

**McDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**ENGINE**

**LARGE AIRCRAFT**

**2002-13-10 McDonnell Douglas:** Amendment 39-12798. Docket
2001-NM-46-AD.

**Applicability:** Model DC-10-10, -10F, -15, -30, -30F, -30F (KC10A and
KDC-10), -40, and -40F airplanes, and Model MD-10-10F and -30F
airplanes; as listed in Boeing Alert Service Bulletin DC10-28A228,
including Appendix, Revision 01, dated July 16, 2001; and Model MD-11
and -11F airplanes, as listed in Boeing Alert Service Bulletin
MD11-28A112, including Appendix, dated December 11, 2000; certificated
in any category.

**Note 1:** Airplane fuel tanks on which the fuel/boost pump and wiring
connector have been physically removed and the fuel tank made inoperable
are NOT subject to the requirements of this AD.

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

**Compliance:** Required as indicated, unless accomplished previously.

To prevent arcing of connectors of the fuel boost/transfer pump, which
could result in a fire or explosion of the fuel tank, accomplish the
following:

**Repetitive Tests and Inspections**

\(a\) Within 6 months after the effective date of this AD, do tests
(using a digital multi-meter and Quadtech 1864 megohm meter or an
equivalent megohm meter that meets current and voltage requirements, as
specified in the applicable service bulletin) for electrical continuity
and resistance and general visual inspections to detect discrepancies
(e.g., damage, arcing, loose parts, wear) of the fuel boost/transfer
pump (alternating current pumping unit) by accomplishing all the actions
specified in the Accomplishment Instructions of Boeing Alert Service
Bulletin MD11-28A112, including Appendix, dated December 11, 2000 (for
Model MD-11 and -11F airplanes); or Boeing Alert Service Bulletin
DC10-28A228, including Appendix, dated December 11, 2000, or Revision
01, dated July 16, 2001, or Revision 02, dated December 7, 2001 (for
Model DC-10-10, -10F, -15, -30, -30F, -30F (KC10A and KDC-10), -40, and
-40F airplanes, and Model MD-10-10F and -30F airplanes); as applicable.
Repeat the tests and inspections thereafter every 18 months.

**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.\'\'

**Corrective Actions, If Necessary**

\(b\) If the result of any test required by paragraph (a) of this AD is
outside the limits specified in the applicable service bulletin
identified in that paragraph, or if any discrepancy is detected during
any inspection required by paragraph (a) of this AD, before further
flight, accomplish corrective actions (e.g., replacement of
connector/wire assembly with serviceable connector/wire assembly, and
replacement of the pump with a serviceable fuel boost/transfer pump), as
applicable, in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin MD11-28A112, including Appendix, dated December
11, 2000 (for Model MD-11 and -11F airplanes); or Boeing Alert Service
Bulletin DC10-28A228, including Appendix, dated December 11, 2000,
Revision 01, dated July 16, 2001, or Revision 02, dated December 7, 2001
(for Model DC-10-10, -10F, -15, -30, -30F, -30F (KC10A and KDC-10), -40,
and -40F airplanes, and Model MD-10-10F and -30F airplanes); as
applicable.

**Alternative Methods of Compliance**

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

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

**Special Flight Permits**

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

**Incorporation by Reference**

\(e\) The actions shall be done in accordance with Boeing Alert Service
Bulletin MD11-28A112, including Appendix, dated December 11, 2000;
Boeing Alert Service Bulletin DC10-28A228, including Appendix, dated
December 11, 2000; Boeing Alert Service Bulletin DC10-28A228, including
Appendix, Revision 01, dated July 16, 2001; or Boeing Alert Service
Bulletin DC10-28A228, including Appendix, Revision 02, dated December 7,
2001; as applicable. This incorporation by reference was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. Copies may be obtained from Boeing Commercial Aircraft
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Data

and Service Management, Dept. C1-L5A (D800-0024). Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue
SW., Renton, Washington; at the FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office
of the Federal Register, 800 North Capitol Street NW., Suite 700,
Washington, DC.

**Effective Date**

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

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Philip C.
Kush, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
California 90712; telephone (562) 627-5263; fax (562) 627-5210.

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

Issued in Renton, Washington, on June 25, 2002.

Kalene C. Yanamura,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-16531 Filed 7-5-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-14**

**McDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-13-12 McDonnell Douglas:** Amendment 39-12800. Docket
2002-NM-36-AD. Supersedes AD 2001-24-15, Amendment 39-12532.

**Applicability:** Model DC-9-10, -30, -30F, and -40 series airplanes,
and Model C-9 airplanes; certificated in any category; as listed in
McDonnell Douglas Alert Service Bulletin DC9-33A058, Revision 03, dated
November 21, 2001; and equipped with an attendants\' work light in the
aft cabin.

**Note 1:** This AD applies to each airplane identified in the preceding
applicability provision, regardless of whether it has been modified,
altered, or repaired in the area subject to the requirements of this AD.
For airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (c)(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 arcing or arcing damage to the wiring of the attendants\'
work light of the aft cabin due to chafing of the ground wire against
the positive contact of the lamp of the attendants\' work light and
transformer of the aft cabin, which could result in short circuits and
consequent smoke and fire in the aft cabin area, accomplish the
following:

**Note 2:** Paragraph (a) of this AD merely restates the requirements of
paragraph (a) of AD 2001-24-15, amendment 39-12532. As allowed by the
phrase, \'\'unless accomplished previously,\'\' if those requirements of
AD 2001-24-15 have already been accomplished, this AD does not require
that those actions be repeated.

**Restatement of AD 2001-24-15**

\(a\) For airplanes listed in McDonnell Douglas Alert Service Bulletin
DC9-33A058, Revision 02, dated January 27, 2000: Within 1 year after
January 16, 2002 (the effective date of AD 2001-24-15), do the actions
specified in paragraphs (a)(1) and (a)(2) of this AD, per McDonnell
Douglas Alert Service Bulletin DC9-33A058, Revision 02, dated January
27, 2000.

\(1\) Do a general visual inspection to detect chafing of the wiring of
the attendants\' work light of the aft cabin. If any chafing is
detected, before further flight, repair chafed wiring per the service
bulletin.

**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.\'\'

\(2\) Modify and reidentify the attendants\' work light assemblies of
the aft cabin.

**New Requirements of This AD**

\(b\) For airplanes listed in McDonnell Douglas Alert Service Bulletin

DC9-33A058, Revision 03, dated November 21, 2001: Within 1 year after
the effective date of this AD, do the actions specified in paragraphs
(b)(1) and (b)(2) of this AD, per McDonnell Douglas Alert Service
Bulletin DC9-33A058, Revision 03, dated November 21, 2002.

\(1\) Do a general visual inspection to detect chafing of the wiring of
the attendants\' work light of the aft cabin. If any chafing is
detected, before further flight, repair chafed wiring per the service
bulletin.

\(2\) Modify and reidentify the attendants\' work light assemblies of
the aft cabin.

**Note 4:** Inspections, repairs, modifications, and reidentifications
done before the effective date of this AD per McDonnell Douglas Service
Bulletin DC9-33-058, dated June 5, 1973; Revision 1, dated November 26,
1975; or Revision 02, dated January 27, 2000; are considered acceptable
for compliance with the requirements of this AD.

**Alternative Methods of Compliance**

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

\(2\) Alternative methods of compliance, approved previously in
accordance with AD 2001-24-15, are approved as alternative methods of
compliance with paragraph (a) of this AD.

**Note 5:** Information concerning the existence of approved alternative
methods of compliance with this AD, if any, may be obtained from the Los
Angeles ACO.

**Special Flight Permits**

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

**Incorporation by Reference**

\(e\) The actions shall be done in accordance with McDonnell Douglas
Alert Service Bulletin DC9-33A058, Revision 02, dated January 27, 2000;
and McDonnell Douglas Alert Service Bulletin DC9-33A058, Revision 03,
dated November 21, 2001; as applicable.

\(1\) The incorporation by reference of McDonnell Douglas Alert Service
Bulletin DC9-33A058, Revision 03, dated November 21, 2001, is approved
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.

\(2\) The incorporation by reference of McDonnell Douglas Alert Service
Bulletin DC9-33A058, Revision 02, dated January 27, 2000, was approved
previously by the Director of the Federal Register as of January 16,
2002 (66 FR 64133, December 12, 2001).

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

**Effective Date**

\(f\) This amendment becomes effective on August 13, 2002.

**FOR FURTHER INFORMATION CONTACT:**

Technical Information: Elvin Wheeler, Aerospace Engineer, Systems and
Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5344; fax (562) 627-5210.

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

Issued in Renton, Washington, on June 26, 2002.

Kalene C. Yanamura,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-16677 Filed 7-8-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-14**

**BOEING**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-02 Boeing:** Amendment 39-12802. Docket 2002-NM-108-AD.

**Applicability:** Model 767-300 series airplanes, line numbers 001
through 810 inclusive, certificated in any category, and equipped with
Rolls Royce RB211-524H series engines.

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

**Compliance:** Required as indicated, unless accomplished previously.

To ensure that control wiring for the thrust reverser actuation system
is adequately separated in order to prevent a single failure from
resulting in uncommanded deployment of a thrust reverser and consequent
reduced controllability of the airplane, accomplish the following:

**Re-Routing of Wire Bundle and Functional Test**

\(a\) Within 36 months after the effective date of this AD, re-route
wire bundle W518 (which is located along the leading edge of the right
wing from the outboard pressure seal to the wing/strut disconnect),
according to Boeing Service Bulletin 767-78-0085, dated November 8,
2001. Before the next flight after the re-routing, the functional test
specified in the procedures in the service bulletin must be successfully
completed.

**Alternative Methods of Compliance**

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

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

**Special Flight Permits**

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

**Incorporation by Reference**

\(d\) The actions shall be done in accordance with Boeing Service
Bulletin 767-78-0085, dated November 8, 2001. This incorporation by
reference was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
the Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.

**Effective Date**

\(e\) This amendment becomes effective on July 29, 2002.

**FOR FURTHER INFORMATION CONTACT:** Technical Information: Dan Kinney,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington
98055-4056; telephone (425) 227-2666; fax (425) 227-1181.

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

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

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17244 Filed 7-11-02; 8:45 am\]

BILLING CODE 4910-13-P

**BW 2002-14**

**McDONNELL DOUGLAS**

**AIRWORTHINESS DIRECTIVE**

**LARGE AIRCRAFT**

**2002-14-16 McDonnell Douglas:** Amendment 39-12816. Docket
2001-NM-244-AD.

**Applicability:** Model 717-200 airplanes, manufacturer\'s fuselage
numbers 5002 through 5064 inclusive, and 5066 through 5073 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 (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD; and,
if the unsafe condition has not been eliminated, the request should
include specific proposed actions to address it.

**Compliance:** Required as indicated, unless accomplished previously.

To detect and correct as well as to prevent cracks in the spoiler
hold-down actuator supports, which could lead to reduced spoiler
hold-down capability, resulting in loss of the back-up protection of the
spoiler float hold-down and unavailability of monitoring for an
uncommanded spoiler movement, accomplish the following:

**Initial Inspection**

\(a\) Prior to the accumulation of 1,500 total flight hours (FH) or
within 500 FH after the effective date of this AD, whichever occurs
later: Perform a detailed inspection of the spoiler hold-down actuator
supports on the left and right wing rear spar for cracks, in accordance
with Boeing Alert Service Bulletin 717-57A0002, Revision 02, dated
October 2, 2001.

\(1\) If no crack is detected: Prior to further flight, adjust the
spoiler hold-down actuators in accordance with the service bulletin.

\(2\) If any crack is detected: Prior to further flight, adjust the
spoiler hold-down actuators in accordance with the service bulletin.
Within 500 flight hours after accomplishment of the inspection, replace
the cracked spoiler hold-down actuator supports and associated idler
link(s), hinge pins, and attaching parts with new parts and adjust the
spoiler hold-down actuators, in accordance with Boeing Service Bulletin
717-57-0004, Revision 01, dated October 2, 2001. Replacement of a
cracked spoiler hold-down actuator support as required herein
constitutes terminating action for that actuator support for the
requirements of this AD.

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

**Repetitive Inspections**

\(b\) If the initial inspection required by paragraph (a) of this AD
does not detect cracks, repeat the detailed inspection of the spoiler
hold-down actuator support, in accordance with Boeing Alert Service
Bulletin 717-57A0002, Revision 02, dated October 2, 2001, at intervals
not to exceed 500 flight hours until the accomplishment of the
requirements of paragraph (d) of this AD.

\(c\) If a detailed inspection for cracks of a spoiler hold-down
actuator support was performed and the actuator was adjusted prior to
the effective date of this AD, in accordance with Boeing Alert Service
Bulletin 717-57A0002, Revision 01, dated February 28, 2001, repeat the
detailed inspection in accordance with Boeing Alert Service Bulletin
717-57A0002, Revision 02, dated October 2, 2001, within 500 FH of the
last inspection or within 500 FH of the effective date of this AD,
whichever occurs later.

**Terminating Action**

\(d\) Within 15 months after the effective date of this AD: Replace
spoiler hold-down actuator supports, idler links, hinge pin, and
attaching parts with new parts and adjust the spoiler hold-down
actuators, in accordance with Boeing Service Bulletin 717-57-0004,
Revision 01, dated October 2, 2001. Replacement of all spoiler hold-down
actuators in accordance with Boeing Service Bulletin 717-57-0004,
Revision 01, dated October 2, 2001, constitutes terminating action for
the requirements of this AD.

\(1\) Any spoiler hold-down actuator supports, idler links, hinge pin,
or attaching parts which have previously been replaced in accordance
with paragraph (a)(2) of this AD do not need to be replaced.

\(2\) Any spoiler hold-down actuator supports, idler links, hinge pins,
or attaching parts which were replaced prior to the effective date of
this AD in accordance with Boeing Service Bulletin 717-57-0004, original
issue, dated May 30, 2001, do not need to be replaced.

**Alternative Methods of Compliance**

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

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

**Special Flight Permits**

\(f\) 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**

\(g\) The actions shall be done in accordance with Boeing Alert Service
Bulletin 717-57A0002, Revision 02, dated October 2, 2001; and Boeing
Service Bulletin 717-57-0004, Revision 01, dated October 2, 2001; as
applicable. This incorporation by reference was approved by the Director
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from Boeing Commercial Aircraft Group,
Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California
90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024).
Copies may be inspected at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
California; or at the Office of the Federal Register, 800 North Capitol
Street, NW., suite 700, Washington, DC.

**Effective Date**

\(h\) This amendment becomes effective on August 16, 2002.

**FOR FURTHER INFORMATION CONTACT:** *Technical Information*: Maureen
Moreland, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; telephone (562) 627-5238; fax (562)
627-5210.

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

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

Jeffrey E. Duven,

Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.

\[FR Doc. 02-17299 Filed 7-11-02; 8:45 am\]

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