Document ID: chunk:federal_register_of_legislation:F2006B02877:body:0:p2
Version: federal_register_of_legislation:F2006B02877
Segment Type: other
Provision Reference: 
Character Range: 3049–5983

8 socket head cap screw, and verify that the cap screw is inserted into the hole in the terminal. For the proper power feeder terminal and screw buildup, refer to the Boeing 737-600, -700, -800, -900 AMM,
               Chapter 24-21-71, Page 405, Figure 401 (Sheet 4). The subject power feeder terminal is identified as item (7) and the cap screw as item (12).

               This visual inspection does not require loosening or removing any fasteners. The inspection may require looking through the access hole at a slight angle to see the terminal clearly. The terminal can be identified by its shiny metal finish; the current transformer behind the terminal block is made of plastic with a flat black finish.

           Note 1: For the purposes of this Directive, a general visual inspection is defined as: "A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.''

2.        If the requirement 1 visual inspection reveals that the power feeder terminal and No. 8 socket head cap screw are not assembled as shown in Boeing 737-600, - 700, -800, -900 AMM, Section 24-21-71, Page 405, Figure 401 (Sheet 4), replace the rigid bus assembly with a new assembly, in accordance with the procedures specified in Boeing 737-600, -700, -800, -900 AMM, Section 24-21-22

3.        Perform a torque check of the attachment screws of the power feeder terminals in accordance with the procedures specified in Boeing Maintenance Tip 737 MT
             24-003, dated 14 May 1998.

4.        Replace the PDP rigid bus assemblies with new assemblies having the same part numbers as the removed assemblies, in accordance with the procedures specified in Boeing 737-600, -700, -800, -900 AMM, Chapter 24-21-22.

           Replacement of existing PDP rigid bus assemblies with new, improved PDP rigid bus assemblies having part number 1032181-2 or 1032185-2, as applicable, according to Boeing Service Bulletin 737-24-1128, dated 29 April 1999, constitutes optional terminating action for the Requirements of this Directive.

           Note 3: FAA AD 2001-22-11 Amdt 39-12490 and AD 99-08-03 Amdt 39-11107 refer.

 Compliance: For Requirement 1 - Within 30 days after the effective date of this Directive.

           For Requirement 2 - Prior to further flight, following the Requirement 1 inspection.

           For Requirement 3 - Initially concurrent with Requirement 1 and thereafter at intervals not to exceed 1,000 hours time in service (TIS), in accordance with the maintenance tip, until replacement of existing PDP rigid bus assemblies with new, improved PDP rigid