2019-18-03: Exhaust

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): \n\n2019-18-03 The Boeing Company: Amendment 39-19730; Docket No. FAA- 2019-0696; Product Identifier 2019-NM-136-AD. \n\n(a) Effective Date \n\n\n\tThis AD is effective October 3, 2019. \n\n(b) Affected ADs \n\n\n\tNone. \n\n(c) Applicability \n\n\n\tThis AD applies to all The Boeing Company Model 737 series airplanes, certificated in any category, excluding Model 737-100, - 200, -200C, -300, -400, and -500 series airplanes. \n\n(d) Subject \n\n\n\tAir Transport Association (ATA) of America Code 78, Exhaust. \n\n(e) Unsafe Condition \n\n\n\tThis AD was prompted bya report indicating that alteration of thrust reverser upper locking actuators in accordance with certain data contained in the Boeing aircraft maintenance manual (AMM) could delay or prevent detection of the failure of the locking mechanism of a thrust reverser upper locking actuator. The FAA is issuing this AD to address the potential for an undetected unlocked condition of the thrust reverser upper locking actuator locking mechanism in flight, which could significantly increase the likelihood of an in- flight deployment of the thrust reverser and consequent loss of airplane control. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Maintenance/Inspection Program Revision \n\n\n\tFor all airplanes: Within 30 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable, by removing any steps that change the size of the thrust reverser upper locking actuator lock sensor target. \n\n(h) Prohibition From Altering Locking Actuator Target \n\n\n\tFor all airplanes: As of the effective date of this AD, no person may alter the thrust reverser upper locking actuator lock sensor target by grinding or trimming or otherwise removing material from the lock sensor target. \n\n(i) Actuator Integrity Test \n\n\n\tFor Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes: Within 90 days after the effective date of this AD, conduct an integrity test of the thrust reverser upper locking actuator on all 4 locking actuators on the airplane. The integrity test must include at least the steps specified in figure 1 to paragraphs (i) and (k) of this AD. The integrity test is not required to be completed for all 4 actuators in one maintenance visit, provided all 4 actuators are tested within the compliance times specified in this paragraph. During the test, a slight movement from fully stowed on the lower portion of the thrust reverser is acceptable due to the wind up in the flexible shafts between the synchronization lock and the upper actuator lock. \n\n((Page 49008)) \n\n(GRAPHIC) (TIFF OMITTED) TR18SE19.000 \n\n\n\n\n\tNote 1 to paragraph (i): Additional guidance for the integrity test can be found in Boeing 737 AMM Task 78-31-03. \n\n(j) Repetitive Test Interval \n\n\n\tAfter the initial integrity test required by paragraph (i) of this AD, repeat the test thereafter at intervals not to exceed 750 flight hours. \n\n(k) Corrective Action for Failed Integrity Test \n\n\n\tIf, during any integrity test required by paragraph (i) or (j) of this AD, the movement of the thrust reverser exceeds the acceptable ''slight movement'' described in paragraph (i) of this AD, replace the locking actuator before further flight. \n\n(l) Parts Installation Prohibition \n\n\n\tFor airplanes identified in paragraph (c) of this AD, excluding Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes: As of the effective date of this AD, no person may install athrust reverser upper locking actuator part number 315A2801-1, -2, -3, -4, or -5. \n\n(m) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (n) of this AD. Information may be emailed to: [email protected]. \n\t(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. \n\t(3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this ADif it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. \n\n(n) Related Information \n\n\n\tFor more information about this AD, contact Christopher Baker, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231- 3552; email: [email protected]. \n\n(o) Material Incorporated by Reference \n\n\n\tNone.