Airworthiness Directive · Amendment 39-14552 · McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-50, -60, -60F, -70, and -70F Series Airplanes; Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-8
McDonnell Douglas Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 Airplanes; Model DC-8F-54 and DC-8F-55 Airplanes; Model DC-8-50, -60, -60F, -70, and -70F Series Airplanes; Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; and Model MD-8
Superseded. A later AD replaced this one: AD 2008-03-12. Comply with the one in force.
This AD applies to the airplanes listed in Table 1 of this AD, certificated in any category.
| McDonnell Douglas | As identified in- |
|---|---|
| Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-51, DC-8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-63 airplanes; Model DC-8-61F, DC-8-62F, and DC-8-63F airplanes; Model DC-8-71, DC-8-72, and DC-8-73 airplanes | McDonnell Douglas DC-8 Alert Service Bulletin A27-273, dated May 16, 1989. |
| Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41 airplanes; Model DC-9-51 airplanes; DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes | McDonnell Douglas DC-9 Alert Service Bulletin Model A27-307, Revision 6, dated December 19, 1994. |
The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas airplanes, as listed above. That AD currently requires an initial general visual or dye penetrant inspection, repetitive dye penetrant inspections, and replacement, as necessary, of the rudder pedal bracket. This new AD also requires, for certain airplanes, replacing the rudder pedal bracket assemblies with new, improved parts, which terminates the repetitive inspections. This AD results from a report of numerous cracked rudder pedal brackets found during inspections of certain affected airplanes. We are issuing this AD to prevent failure of the rudder pedal bracket assembly, which could result in the loss of rudder and braking control at either the captain's or first officer's position.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Prior to the accumulation of 40,000 total landings or within 30 days after July 5, 1989 (the effective date of AD 89-14-02), whichever occurs later, perform either a general visual inspection or dye penetrant inspection for cracks of the captain's and first officer's rudder pedal bracket, part numbers (P/N) 5616067 and 5616068, respectively, in accordance with McDonnell Douglas DC-8 Alert Service Bulletin A27-273 (for Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-51, DC-8-52, DC-8-53, and DC-8-55 airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-61, DC-8-62, and DC-8-63 airplanes; Model DC-8-61F, DC-8-62F, and DC-8-63F airplanes; Model DC-8-71, DC-8-72, and DC-8-73 airplanes), or McDonnell Douglas DC-9 Alert Service Bulletin A27-307 (for Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41 airplanes; Model DC-9-51 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes), both Revision 1, both dated May 16, 1989, as applicable.
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.”
Note 2: McDonnell Douglas DC-8 Alert Service Bulletin A27-273 and McDonnell Douglas DC-9 Alert Service Bulletin A27-307, both Revision 1, both dated May 16, 1989, are hereinafter referred to as ASB A27-273 and ASB A27-307, respectively.
(1) If an initial general visual inspection is accomplished, and no cracks are found, perform a dye penetrant inspection of the rudder pedal bracket assembly within 180 days after the general visual inspection, and thereafter accomplish dye penetrant inspections at intervals not to exceed 12 months or 2,500 landings, whichever occurs earlier.
(2) If an initial dye penetrant inspection is accomplished, and no cracks are found, accomplish repetitive dye penetrant inspections at intervals not to exceed 12 months or 2,500 landings, whichever occurs earlier.
(g) If cracks are detected, prior to further flight, remove and replace the rudder pedal bracket assembly in accordance with ASB A27-273 or A27-307, as applicable. Prior to the accumulation of 40,000 total landings after replacement with the new part, resume the repetitive inspections in accordance with paragraph (f) in this AD.
For McDonnell Douglas Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; Model DC-9-41 airplanes; Model DC-9-51 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes: Do the actions in paragraphs (h)(1) and (h)(2) of this AD in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Alert Service Bulletin A27-307, Revision 4, dated June 3, 1991; Revision 5, dated February 14, 1992; or Revision 6, dated December 19, 1994.
(1) Before the accumulation of 75,000 total landings on the captain's rudder pedal bracket assembly, P/N 5616067-501, or within 60 months after the effective date of this AD, whichever occurs later: Remove the rudder pedal bracket assembly and replace it with new, improved P/N 5962903-501. Accomplishment of the replacement terminates the repetitive inspections of the captain's rudder pedal bracket assembly required by paragraphs (f) and (g) of this AD.
(2) Before the accumulation of 75,000 total landings on the first officer's rudder pedal bracket assembly, P/N 5616068-501, or within 60 months after the effective date of this AD, whichever occurs later: Remove the rudder pedal bracket assembly and replace it with new, improved P/N 5962904-501. Accomplishment of the replacement terminates the repetitive inspections of the first officer's rudder pedal bracket assembly required by paragraphs (f) and (g) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
