Airworthiness Directive · Amendment 39-13789 · McDonnell Douglas Model DC-9-14, DC-9-15, and DC-9-15F Airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes
McDonnell Douglas Model DC-9-14, DC-9-15, and DC-9-15F Airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes
Model 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; as listed in Boeing Service Bulletin DC9-57-225, dated December 10, 2002; certificated in any category.
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-14, DC-9-15, and DC- 9-15F airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This amendment requires, among other actions, performing repetitive inspections for cracking of the counterbore of the two lower mounting holes and the lower forward edge of the outboard idler hinge fitting of the left and right wing flap at station Xw=333.148, and replacing the flap idler hinge fitting with a new or serviceable part. This action is necessary to prevent failure of the outboard idler hinge fitting of the left and right wing flap at station Xw=333.148 due to fatigue cracking, which could result in a deflected flap that may cause asymmetric lift and consequent reduced controllability and structural integrity of the airplane. This action is intended to address the identified unsafe condition.
To prevent failure of the outboard idler hinge fitting of the left and right wing flap at station Xw=333.148 due to fatigue cracking, which could result in a deflected flap that may cause asymmetric lift and consequent reduced controllability and structural integrity of the airplane, accomplish the following:
(a) Prior to the accumulation of 40,000 total landing cycles on the outboard idler hinge fitting of the left and right wing flap at station Xw=333.148, or within 8,000 landing cycles on the fitting after the effective date of this AD, whichever occurs later: Do high frequency eddy current (HFEC) inspections for cracking of the counterbore of the two lower mounting holes and the lower forward edge of the flap idler hinge fitting at station Xw=333.148, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC9-57-225, dated December 10, 2002. Although the service bulletin specifies to report inspection findings to the airplane manufacturer, this AD does not include that requirement.
(b) If no crack is found during any inspection required by paragraph (a) of this AD, prior to further flight, install a new nut, plain washer, and pre-load indicating (PLI) washer in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC9-57-225, dated December 10, 2002. Repeat the inspections required by paragraph (a) of this AD thereafter at intervals not to exceed 1,000 landings on the fitting until the replacement required by paragraph (e) of this AD is done.
(c) If any crack is found during any inspection required by this AD: Before further flight, replace the cracked flap idler hinge fitting with a new or serviceable fitting having a part number identified under the “New Part Number” column of the applicable table shown in paragraph 2.C.1. of the Material Information section of Boeing Service Bulletin DC9-57-225, dated December 10, 2002. Do the replacement in accordance with the Accomplishment Instructions of the service bulletin.
(d) Prior to the accumulation of 40,000 total landing cycles on any new or serviceable fitting, do the HFEC inspections required by paragraph (a) of this AD. Repeat the HFEC inspections thereafter at intervals not to exceed 1,000 landing cycles on the fitting until the replacement required by paragraph (e) of this AD is done.
(e) Prior to the accumulation of 80,500 total landing cycles on the flap idler hinge fitting, replace the fitting with a new or serviceable fitting having a part number identified under the “New Part Number” column of the applicable table shown in paragraph 2.C.1. of the Material Information section of Boeing Service Bulletin DC9-57-225, dated December 10, 2002. Do the replacement in accordance with the Accomplishment Instructions of the service bulletin. Repeat the replacement thereafter at intervals not to exceed 80,500 total landing cycles on the fitting.
(f) In accordance with 14 CFR 39.19, the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance (AMOCs) for 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.
