Airworthiness Directive · Amendment 39-13867 · Boeing Model 757-200 and -300 Series Airplanes
Boeing Model 757-200 and -300 Series Airplanes
Model 757-200 series airplanes, as listed in Boeing Special Attention Service Bulletin 757-52-0077, dated February 15, 2001; and Model 757-300 series airplanes, as listed in Boeing Special Attention Service Bulletin 757-52-0078, dated February 15, 2001; certificated in any category.
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -300 series airplanes. This AD requires inspection of the guide arm assembly on passenger door number 1 left for a part mark to determine whether the guide arm assembly contains an adjuster rod, which was incorrectly manufactured, and replacement of any such adjuster rod. This action is necessary to prevent failure of the adjuster rod in the passenger door guide arm assembly, which could prevent the door from opening or closing during normal or emergency operations, resulting in the inability to evacuate the crew and passengers in an emergency. This action is intended to address the identified unsafe condition.
To prevent failure of the adjuster rod in the passenger door guide arm assembly, which could prevent the door from opening or closing during normal or emergency operations, resulting in the inability to evacuate the crew and passengers in an emergency, accomplish the following:
(a) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of the following service bulletins, as applicable:
(1) For Model 757-200 series airplanes: Boeing Special Attention Service Bulletin 757-52-0077, dated February 15, 2001; and
(2) For Model 757-300 series airplanes: Boeing Special Attention Service Bulletin 757-52-0078, dated February 15, 2001.
(b) Within 18 months of the effective date of this AD: Inspect the part mark on the guide arm assembly of the number 1 left passenger door, in accordance with the applicable service bulletin.
(c) If the inspection of the part mark required by paragraph (b) of this AD reveals the name of a supplier, accomplish the action specified in paragraph (c)(1) or (c)(2) of this AD, as applicable.
(1) If the part mark of supplier CDSL is found on the guide arm assembly, prior to the accumulation of 6,666 total flight cycles, replace the adjuster rod of the guide arm assembly per Figure 2 of the applicable service bulletin.
(2) If the part mark of a supplier other than CDSL is found on the guide arm assembly, then the adjuster rod is satisfactory, and no further action is required by this paragraph.
(d) If no part mark is found during the inspection required by paragraph (b) of this AD, prior to the accumulation of 6,666 total flight cycles, accomplish the action specified in either paragraph (d)(1) or (d)(2) of this AD.
(1) Replace the adjuster rod of the guide arm assembly per Figure 2 of the applicable service bulletin.
(2) Test the hardness of the adjuster rod of the guide arm assembly per Figure 3 of the applicable service bulletin; and do the action specified in paragraph (d)(2)(i) or (d)(2)(ii) of this AD, as applicable.
(i) If the hardness of the adjuster rod is less than 44 HRC (Rockwell C Hardness scale), prior to the accumulation of 6,666 total flight cycles, replace the adjuster rod of the guide arm assembly per Figure 2 of the applicable service bulletin.
(ii) If the hardness of the adjuster rod is greater than 44 HRC, then the adjuster rod is satisfactory, and no further action is required by this paragraph.
(e) In accordance with 14 CFR 39.19, the Manager, Seattle Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance 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.
Aircraft
