Airworthiness Directive · Amendment 39-14598 · McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 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; Model MD-88 Airplanes; Model MD-90-30 Airplanes; and Model 717-200 Airplanes
McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 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; Model MD-88 Airplanes; Model MD-90-30 Airplanes; and Model 717-200 Airplanes
This AD applies to the airplanes specified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.
(1) All McDonnell Douglas Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and 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; Model MD-88 airplanes; and Model MD-90-30 airplanes; and
(2) Model 717-200 airplanes, as identified in Boeing Service Bulletin 717-52-0007, Revision 1, dated March 2, 2006.
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires an inspection to determine the part number of the upper and lower stop pad support fittings of all the lower cargo doors, repetitive inspections of all early configuration stop pad support fittings, and corrective action if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from a report of cracks found in the area of the upper and lower stop pad support fittings of the cargo door pan on numerous airplanes. We are issuing this AD to prevent cracks in the cargo door pan, which could result in the inability to fully pressurize an airplane, possible pressure loss, or possible rapid decompression of the airplane.
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 following service bulletins, as applicable:
(1) For Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and 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: Boeing Service Bulletin DC9-52-189, Revision 2, dated December 20, 2005;
(2) For Model MD-90-30 airplanes: Boeing Service Bulletin MD90-52-014, Revision 1, dated March 22, 2006; and
(3) For Model 717-200 airplanes: Boeing Service Bulletin 717-52-0007, Revision 1, dated March 2, 2006.
For the airplanes identified in Table 1 of this AD: At the compliance time specified in Table 1 of this AD, inspect to determine the part number of the upper and lower stop pad support fittings of the lower cargo doors, in accordance with the Accomplishment Instructions of the service bulletin, as applicable. If new configuration or new upper and lower stop pad support fittings, as identified in the applicable service bulletin, are found installed on all lower cargo doors, then no further action is required by this paragraph. If any early configuration stop pad support fitting is found installed on any lower cargo door, at the applicable compliance time specified in Table 1 of this AD, do the inspection specified in either paragraph (g)(1) or (g)(2) of this AD, in accordance with the Accomplishment Instructions of the service bulletin, until the replacement specified in paragraph (k) of this AD is accomplished.
(1) Do a general visual inspection for cracks in any lower cargo door having an early configuration stop pad support fitting. Repeat the general visual inspection thereafter at intervals not to exceed 1,700 flight cycles.
(2) Do an eddy current inspection for cracks in any lower cargo door having an early configuration stop pad support fitting. Repeat the eddy current inspection thereafter at intervals not to exceed 3,900 flight cycles.
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.”
| Applicable airplanes | Inspection to determine P/N | Initial inspection of early configuration stop pad support fitting, if applicable |
|---|---|---|
| Airplanes identified as Group 2, 3, and 4 in paragraph 1.A. of Boeing Service Bulletin DC9-52-189, Revision 2, dated December 20, 2005 | Within 18 months after the effective date of this AD | Before further flight. |
| Model MD-90-30 airplanes and Model 717-200 airplanes | Before the accumulation of 25,000 total flight cycles, or within 3,900 flight cycles after the effective date of this AD, whichever is later | Within 300 flight hours. |
For the airplanes identified as Group 1 in paragraph 1.A. of Boeing Service Bulletin DC9-52-189, Revision 2, dated December 20, 2005: At the applicable compliance time specified in Table 2 of this AD, do the inspection specified in either paragraph (g)(1) or (g)(2) of this AD, in accordance with the Accomplishment Instructions of the applicable service bulletin. Repeat the inspection thereafter at the interval specified in paragraph (g)(1) or (g)(2), as applicable, until the replacement specified in paragraph (k) of this AD is accomplished. Inspections also may be done in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 52-89, Revision 5, dated February 26, 1991; or Revision 6, dated January 11, 1993.
| For airplanes that have— | Compliance time |
|---|---|
| Been inspected before the effective date of this AD in accordance with paragraph (b) of AD 96-10-11 as specified in Phase I of the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 52-89, Revision 5, dated February 26, 1991; or Revision 6, dated January 11, 1993 | Within 1,700 flight cycles after the last general visual inspection, or within 3,900 flight cycles after the last eddy current inspection, as applicable. |
| Not been inspected before the effective date of this AD in accordance with paragraph (b) of AD 96-10-11 as specified in Phase I of the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 52-89, Revision 5, dated February 26, 1991; or Revision 6, dated January 11, 1993 | Within 18 months after the effective date of this AD. |
(i) For Model MD-90-30 airplanes and Model 717-200 airplanes: If any crack is found in the door jamb or jamb structure of a lower cargo door during any inspection required by paragraph (g)(1) or (g)(2) of this AD, and the service bulletin specifies contacting Boeing for appropriate action, before further flight, repair the crack using a method in accordance with the procedures specified in paragraph (o) of this AD.
For Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, 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: If any crack is found during any inspection required by paragraph (g)(1), (g)(2), or (h) of this AD, do the corrective action at the applicable compliance time specified in paragraph 1.E. of the service bulletin, in accordance with the Accomplishment Instructions of the service bulletin, as applicable.
For all airplanes: Replacement of all early configuration stop pad support fittings installed on a lower cargo door with new configuration or new stop pad support fittings, as identified in the applicable service bulletin; and reidentification of the applicable lower cargo door; in accordance with the Accomplishment Instructions of the applicable service bulletin; terminates the repetitive inspections required by paragraphs (g)(1), (g)(2), and (h) of this AD, as applicable, for that lower cargo door only.
For all airplanes: As of the effective date of this AD, no person may install an early configuration stop pad support fitting having P/N 3925046-1, -501, -505, -507, or -509, or P/N 3926046-1 or -501, on any airplane.
Actions done before the effective date of this AD in accordance with the applicable service bulletin specified in paragraph (m)(1), (m)(2), or (m)(3) of this AD, are acceptable for compliance with the corresponding requirements of this AD.
(1) Boeing Service Bulletin DC9-52-189, dated August 10, 2001; or Revision 01, dated March 20, 2003.
(2) Boeing Service Bulletin MD90-52-014, dated December 14, 2004.
(3) Boeing Service Bulletin 717-52-0007, dated December 14, 2004, except where the service bulletin refers to Chapter 52-31-00 of the Boeing 717 Aircraft Maintenance Manual for instructions on adjusting the forward and aft lower cargo doors, instead refer to Chapter 52-31-01 for those instructions.
For Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and DC-9-51 airplanes: Accomplishing the replacement specified in paragraph (k) of this AD for the forward and aft lower cargo doors terminates the repetitive inspections of the forward and aft lower cargo doors for cracks required by paragraph (b) of AD 96-10-11 as specified in McDonnell Douglas DC-9 Service Bulletin 52-89, Revision 5, dated February 26, 1991.
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.
