Airworthiness Directive · Amendment 39-15362 · 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
This AD applies to the airplanes identified 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; Model DC-8-71F, DC-8-72F, and DC-8-73F airplanes | McDonnell Douglas DC-8 Alert Service Bulletin A27-273, Revision 5, dated February 18, 1993. |
| 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 | Boeing Alert Service Bulletin DC9-27A307, Revision 7, dated August 29, 2006. |
The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas airplanes. The existing AD currently requires an initial general visual or dye penetrant inspection, repetitive dye penetrant inspections, and replacement, as necessary, of the rudder pedal bracket. The existing AD also currently requires, for certain airplanes, replacing the rudder pedal bracket assemblies with new, improved parts, which would terminate the repetitive inspections. For certain airplanes, this new AD requires initial inspection at a reduced threshold, removes an inspection option, and lengthens the repetitive inspection intervals. This AD results from reports of failures of the captain's rudder pedal brackets before reaching the initial inspection threshold identified in the existing AD. 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.
The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD. The term “airplane category,” as used in this AD, means the category identified in Table 2 of this AD.
| For Model— | Called airplane category— | Use— |
|---|---|---|
| (1) 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 | 1 | McDonnell Douglas DC-8 Alert Service Bulletin A27-273, Revision 1, dated May 16, 1989; or Revision 5, dated February 18, 1993. |
| (2) DC-8-71F, DC-8-72F, and DC-8-73F airplanes | 2 | |
| (3) 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 | 3 | McDonnell Douglas DC-9 Alert Service Bulletin A27-307, Revision 1, dated May 16, 1989; or Boeing Alert Service Bulletin DC9-27A307, Revision 7, dated August 29, 2006, after the effective date of this AD, only Revision 7 may be used. |
| (4) 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 | 4 |
For airplane categories 1, 3, and 4, 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, amendment 39-6245, which was superseded by AD 2006-07-25), whichever occurs later: Perform either a general visual inspection, dye penetrant inspection, or special detailed inspection (eddy current with dye penetrant or just dye penetrant), as applicable, for cracking of the captain's and first officer's rudder pedal bracket, part numbers (P/N) 5616067 and 5616068, respectively, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in Table 2 of this AD. After the effective date of this AD, only the special detailed inspection specified in Boeing Alert Service Bulletin DC9-27A307, Revision 7, dated August 29, 2006, may be used for airplanes identified in Revision 7. For airplane category 4: Do the inspection required by this paragraph until the inspection required by paragraph (j) of this AD is accomplished.
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.”
(1) If an initial general visual inspection is accomplished, and no crack is 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. For airplane categories 3 and 4, repeat at this interval until the inspection required by paragraph (k) of this AD is accomplished.
(2) If an initial dye penetrant inspection is accomplished, and no crack is found, accomplish repetitive dye penetrant inspections at intervals not to exceed 12 months or 2,500 landings, whichever occurs earlier. For airplane categories 3 and 4, repeat at this interval until the inspection required by paragraph (k) of this AD is accomplished.
(3) If an initial special detailed inspection is accomplished after the effective date of this AD, and no crack is found, repeat the inspection in accordance with paragraph (k) of this AD.
Except as provided by paragraph (l) of this AD: If any crack is detected during any inspection required by paragraph (g) or (j) of this AD, before further flight, remove and replace the rudder pedal bracket assembly in accordance with the service bulletin. Prior to the accumulation of 40,000 total landings after replacement with a part that has the same number as the part inspected, resume the repetitive inspections in accordance with paragraph (g) or (k) of this AD, as applicable. Doing the action required by paragraph (l) of this AD terminates the requirements of this paragraph for airplane category 4.
(i) For airplane categories 3 and 4: Do the actions in paragraphs (i)(1) and (i)(2) of this AD in accordance with the Accomplishment Instructions of the applicable service bulletin specified in Table 2 of this AD.
(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 May 16, 2006, 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 (g), (h), (j), (k), and (l) 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 May 16, 2006, 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 (g), (h), (j), (k), and (l) of this AD.
For airplane categories 2 and 4, at the applicable time specified in paragraph (j)(1), (j)(2) or (j)(3) of this AD: Do a general visual and penetrant inspection (for airplane category 2), and a special detailed inspection (for airplane category 4), as applicable, to detect cracking of the captain's and first officer's rudder pedal bracket, part numbers (P/N) 5616067 and 5616068, respectively, in accordance with the applicable service bulletin specified in Table 2 of this AD. Procedures for the dye penetrant inspection for airplane category 2 are contained only in the Accomplishment Instructions of McDonnell Douglas DC-8 Alert Service Bulletin A27-273, Revision 1, dated May 16, 1989. Procedures for the special detailed inspection are contained in Boeing Alert Service Bulletin DC9-27A307, Revision 7, dated August 29, 2006. Doing the applicable inspection required by this paragraph terminates the inspection requirements of paragraphs (g) and (h) of this AD for airplane category 4.
(1) For category 2 airplanes: Before the accumulation of 40,000 total landings on the installed part, or within 30 days after the effective date of this AD, whichever occurs later.
(2) For category 4 airplanes that have accumulated fewer than 25,000 total landings as of the effective date of this AD: Before the accumulation of 25,000 total landings, or within 3,000 landings after the effective date of this AD, whichever occurs later.
(3) For category 4 airplanes that have accumulated 25,000 or more total landings as of the effective date of this AD, do the next inspection at the applicable time in paragraph (j)(3)(i) or (j)(3)(ii) of this AD.
(i) For category 4 airplanes on which the corrective action specified in paragraph (h) of this AD has not been accomplished, do the inspection within 3,000 landings after the effective date of this AD.
(ii) For category 4 airplanes on which the corrective action required by paragraph (h) of this AD has been accomplished, do the inspection at the earlier of the following: The next repetitive interval required by paragraph (h) of this AD; 40,000 total landings after doing the corrective action required by paragraph (h) of this AD; or 3,000 landings after the effective date of this AD.
For airplane categories 3 and 4: Repeat the special detailed inspection required by paragraph (g) or (j) of this AD thereafter at intervals not to exceed 3,000 landings. Doing the first repetitive inspection required by this paragraph terminates the repetitive inspection requirements of paragraph (g) of this AD for airplane categories 3 and 4.
For airplane category 4: If any crack is detected during any inspection required by paragraph (g), (j), or (k) of this AD: Before further flight, remove and replace the rudder pedal bracket assembly with a part that has the same part number as the one inspected, in accordance with the applicable service bulletin specified in Table 2 of this AD. Before the accumulation of 25,000 total landings after replacement, resume the repetitive inspections in accordance with paragraph (k) of this AD. Doing the action in this paragraph terminates the requirements of paragraph (h) of this AD for airplane category 4.
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.
