Airworthiness Directive · Amendment 39-15990 · Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes
This AD applies to Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes, certificated in any category; as identified in Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. That AD currently requires replacing brackets that hold the P5 panel to the airplane structure, the standby compass bracket assembly, the generator drive and standby power module, and the air conditioning module, as applicable. The existing AD also currently requires, among other actions, inspecting for wire length and for damage of the connectors and the wire bundles, and doing applicable corrective actions if necessary. This new AD requires an additional operational test of the P5-14 panel. This AD results from a report of an electrical burning smell in the flight compartment. We are issuing this AD to prevent wire bundles from contacting the overhead dripshield panel and modules in the P5 overhead panel, which could result in electrical arcing and shorting of the electrical connector and consequent loss of several critical systems essential for safe flight; and to ensure proper operation of the passenger oxygen system. If an improperly functioning passenger oxygen system goes undetected, the passenger oxygen mask could fail to deploy and result in possible incapacitation of passengers during a depressurization event.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 36 months after June 22, 2006 (the effective date of AD 2006-10-17), do the applicable actions in paragraphs (f)(1) through (f)(5) of this AD by accomplishing all the applicable actions specified in the Accomplishment Instructions of Boeing Service Bulletin 737-24A1141, Revision 2, dated December 1, 2005, except as provided by paragraph (i) of this AD. Any applicable corrective actions must be done before further flight.
(1) Replace the five brackets that hold the P5 panel to the airplane structure with new brackets;
(2) Do a general visual inspection for wire length and damage of the connectors and the wire bundles, and applicable corrective actions;
(3) Make wiring changes;
(4) Replace the standby compass bracket assembly with a new assembly; and
(5) Replace the stud assemblies with new assemblies.
Note 1: For the purposes of this AD, a general visual inspection is: “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 ensure visual access to all 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.”
(g) Actions done before June 22, 2006, in accordance with Boeing Alert Service Bulletin 737-24A1141, Revision 1, dated December 23, 2004, are acceptable for compliance with the requirements of paragraph (f) of this AD.
Before or concurrently with the requirements of paragraph (f) of this AD, do the applicable action specified in Table 1 of this AD.
| For airplanes identified in Boeing component Service Bulletin— | Action |
|---|---|
| (1) 233A3205-24-01, dated July 26, 2001 | Modify the generator drive and standby power module assembly in accordance with the Accomplishment Instructions of Boeing Component Service Bulletin 233A3205-24-01, dated July 26, 2001. |
| (2) 69-37319-21-02, Revision 1, dated August 30, 2001 | Modify the air conditioning module assembly in accordance with the Accomplishment Instructions of Boeing Component Service Bulletin 69-37319-21-02, Revision 1, dated August 30, 2001. |
(i) As of the effective date of this AD, use only the Accomplishment Instructions of Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008, to do all the applicable actions required by paragraph (f) of this AD.
Note 2: Accomplishment of the steps specified in the tables of the figures of Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008, is required. Due to the variability of airplane configurations, the illustrations in the figures are provided as examples.
Note 3: Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008, refers to “unwanted” wire length. “Unwanted” wire length is any wire length that does not meet the wire length requirements specified in the Standard Wiring Practices Manual (SWPM).
For airplanes on which the actions required by paragraph (f) of this AD have been done in accordance with Boeing Service Bulletin 737-24A1141, Revision 2, dated December 1, 2005, before the effective date of this AD: Within 12 months after the effective date of this AD, do an operational test of the P5-14 panel in accordance with paragraphs 3.B.92. and 3.B.93., as applicable, of the Accomplishment Instructions of Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008.
