Airworthiness Directive · Amendment 39-11919 · McDonnell Douglas Model DC-8 Series Airplanes
McDonnell Douglas Model DC-8 Series Airplanes
Model DC-8 series airplanes, as listed in McDonnell Douglas Service Bulletin DC8-53-075, dated August 17, 1995; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (g) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires, for certain airplanes, inspection(s) to detect cracks of the doorjamb corners and follow-on actions. For certain other airplanes, this AD requires installation of a preventative modification; an inspection to detect cracks at the corners of the doorjambs of the passenger and service doors; and follow-on actions. This amendment is prompted by reports indicating that fatigue cracks were found in the fuselage skin and doublers at the corners of the doorjambs of the passenger and service doors. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
To detect and correct fatigue cracking in the fuselage skin and doublers at the corners of the doorjambs of the passenger and service doors, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane, accomplish the following:
Note 2: Where there are differences between the service bulletin and the AD, the AD prevails.
Note 3: The words “repair” and “modify/modification” in this AD and in the referenced service bulletin are used interchangeably.
Note 4: This AD is related to AD 93-01-15, amendment 39-8469, and will affect Principal Structural Elements (PSE) 53.08.038, 53.08.039, 53.08.040, and 53.08.041 of the DC-8 Supplemental Inspection Document (SID), Report L26-011, Volume I, Revision 3, dated March 1991.
(a) For airplanes identified as Group 1 in McDonnell Douglas Service Bulletin DC8-53-075, dated August 17, 1995: Within 2,000 landings or 3 years after the effective date of this AD, whichever occurs first, perform the applicable inspection(s) to detect cracks of the doorjamb corners in accordance with the service bulletin.
(1) If no crack is detected during any inspection required by paragraph (a) of this AD, repeat the applicable inspection(s) required by paragraph (a) of this AD thereafter at intervals specified for Group 1 airplanes in paragraph 1.E. of the service bulletin; or accomplish the preventative modification in accordance with the service bulletin. Accomplishment of the preventative modification constitutes terminating action for the repetitive inspection requirements of this paragraph.
(2) If any crack is detected during any inspection required by paragraph (a) of this AD, prior to further flight, repair in accordance with the service bulletin, except as provided by paragraph (f) of this AD.
(b) Within 17,000 landings following accomplishment of the modification/repair required by either paragraph (a)(1) or (a)(2) of this AD, perform an inspection to detect cracks of the doorjamb corners, in accordance with McDonnell Douglas Service Bulletin DC8-53-075, dated August 17, 1995.
(1) If no crack is detected, repeat the inspection thereafter at intervals not to exceed 4,400 landings.
(2) If any crack is detected, prior to further flight, repair in accordance with the service bulletin, except as provided by paragraph (f) of this AD.
(c) For airplanes identified as Group 2 in McDonnell Douglas Service Bulletin DC8-53-075, dated August 17, 1995: Within 2,000 landings or 3 years after the effective date of this AD, whichever occurs first, accomplish the preventative modification in accordance with the service bulletin. Within 17,000 landings following accomplishment of the preventative modification, perform an inspection to detect cracks of the doorjamb corners, in accordance with the service bulletin.
(1) If no crack is detected during any inspection required by paragraph (c) of this AD, repeat the inspection thereafter at intervals not to exceed 4,400 landings.
(2) If any crack is detected during any inspection required by paragraph (c) of this AD, prior to further flight, repair it in accordance the service bulletin, except as provided by paragraph (f) of this AD.
(d) For airplanes identified as Group 3 in McDonnell Douglas Service Bulletin DC8-53-075, dated August 17, 1995: Within 6 years following accomplishment of the permanent repair or within 3 years after the effective date of this AD, whichever occurs later, revise the FAA-approved maintenance or inspection program to include an inspection program for the doorjamb corners identified in the service bulletin. The new inspection program shall be approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA.
Note 5: Requests for approval of inspection procedures of the permanent repairs that are proposed for inclusion in the FAA-approved maintenance or inspection program, as required by this AD, should include a damage tolerance assessment.
(e) For airplanes identified as Group 4 in McDonnell Douglas Service Bulletin DC8-53-075, dated August 17, 1995: Within 17,000 landings following accomplishment of the modification specified in the service bulletin, perform an inspection to detect cracks of the doorjamb corners, in accordance with the service bulletin.
(1) If no crack is detected during any inspection required paragraph (e) of this AD, repeat the inspection thereafter at intervals not to exceed 4,400 landings.
(2) If any crack is detected during any inspection required by paragraph (e) of this AD, prior to further flight, repair in accordance with the service bulletin, except as provided by paragraph (f) of this AD.
(f) Where McDonnell Douglas Service Bulletin DC8-53-075, dated August 17, 1995, specifies that the manufacturer may be contacted for disposition of certain repair conditions, this AD requires the repair of those conditions to be accomplished in accordance with a method approved by the Manager, Los Angeles ACO.
