AD 2000-03-51 Airworthiness Directives; McDonnell Douglas Model DC-9, Model MD-90-30, Model 717-200, and Model MD-88 Airplanes

Models named: DC-9, Model MD-90-30, Model 717-200, Model MD-88. Read the applicability below — it usually turns on serial or part numbers too.

All Model DC-9, Model MD-90-30, Model 717-200, and Model MD-88 airplanes; 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 (d) 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.

Required as indicated, unless accomplished previously. To prevent loss of pitch trim capability due to excessive wear of the jackscrew assembly of the horizontal stabilizer, which could result in loss of vertical control of the airplane, accomplish the following: Inspections and Test (a) Prior to the accumulation of 650 hours total time-in-service (TTIS), or within 72 hours after the effective date of this AD, whichever occurs later, accomplish the actions required by paragraphs (a)(1), (a)(2), (a)(3), (a)(4), and (a)(5) of this AD; in accordance with Boeing Alert Service Bulletin DC9-27A362 (for Model DC-9 and Model MD-88 airplanes), Boeing Alert Service Bulletin MD90-27A034 (for Model MD-90-30 airplanes), and Boeing Alert Service Bulletin 717-27A0002 (for Model 717-200 airplanes), all dated February 11, 2000. Repeat the inspections, thereafter, at intervals not to exceed 650 flight hours. (1) Perform a general visual inspection of the lubricating grease on the jackscrew assembly and the area directly below the jackscrew and surrounding areas for the presence of metal shavings and flakes in accordance with paragraph 3.B.2. of the Accomplishment Instructions of the applicable alert service bulletin. If the presence of metal shavings or flakes is detected, prior to further flight, remove and replace the jackscrew assembly with a new or serviceable assembly, in accordance with the applicable alert service bulletin. (2) Perform a general visual inspection of the jackscrew assembly to detect the presence of corrosion, pitting, or distress in accordance with paragraph 3.B.3. of the Accomplishment Instructions of the applicable alert service bulletin. If any corrosion, pitting, or distress is detected, prior to further flight, replace the jackscrew assembly with a new or serviceable assembly, in accordance with the applicable alert service bulletin. (3) Check the condition of the jackscrew assembly lubricant in accordance with paragraph 3.B.4. of the Accomplishment Instructions of the applicable alert service bulletin. If the jackscrew assembly is dry, lubricate the assembly in accordance with the applicable alert service bulletin. (4) Inspect the horizontal stabilizer jackscrew upper and lower mechanical stops for general condition in accordance with paragraph 3.B.5. of the Accomplishment Instructions of the applicable alert service bulletin, and record the condition. (5) Perform a test of the horizontal stabilizer shutoff controls in accordance with paragraph 3.B.6. of the Accomplishment Instructions of the applicable alert service bulletin. If the mechanical stop on the jackscrew contacts the mechanical stop on the acme nut prior to limit switch shutoff, prior to further flight, adjust the horizontal stabilizer trim system in accordance with operator-approved maintenance instructions. Note 2: For the purposes of this AD, a general visual inspection is defined as: “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 under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light 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.” Wear Check (b) Within 2,000 flight hours since the last acme screw and nut wear check conducted in accordance with the DC9 McDonnell Douglas Maintenance Manual, Chapter 27-41-1; MD80 McDonnell Douglas Maintenance Manual, Chapter 27-41-01; MD90 McDonnell Douglas Maintenance Manual, Chapter 27-41-10; or 717 McDonnell Douglas Maintenance Manual, Chapter 27-41-04; or within 30 days after the effective date of this AD, whichever occurs later: Perform an acme screw and nut wear check in accordance with paragraph 3.B., Phase 2, paragraph 2. of the Accomplishment Instructions of Boeing Alert Service Bulletin DC9-27A362 (for Model DC-9 and Model MD-88 airplanes), Boeing Alert Service Bulletin MD90-27A034 (for Model MD-90-30 airplanes), and Boeing Alert Service Bulletin 717-27A0002 (for Model 717-200 airplanes), all dated February 11, 2000. Repeat the inspections, thereafter, at intervals not to exceed 2,000 flight hours. Note 3: Accomplishment of paragraphs (c), (d), and (e) of the Boeing Service Engineering Message Number M-7200-00-00456, dated February 9, 2000, constitutes compliance with paragraphs (a)(2), (a)(3), and (a)(4) of this AD. Accomplishment of paragraph (a) of Boeing Service Engineering Message Number M-7200-00-00456 constitutes compliance with paragraph (b) of this AD. Reporting Requirement (c) If any damage is detected during any inspection required by paragraphs (a) and (b) of this AD, within 48 hours after accomplishing the inspections, report the inspection results in accordance with Boeing Alert Service Bulletin DC9-27A362 (for Model DC-9 and Model MD-88 airplanes), Boeing Alert Service Bulletin MD90-27A034 (for Model MD-90-30 airplanes), and Boeing Alert Service Bulletin 717-27A0002 (for Model 717-200 airplanes), all dated February 11, 2000. If no damage is detected during any inspection required by this AD, report the inspection results within 10 days of accomplishing that inspection in accordance with the appropriate alert service bulletin. For airplanes that are inspected after the effective date of this AD, include in the report the serial number of the airplane, the number of total flight hours and flight cycles accumulated on the airplane to the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5320; Fax (562) 627-5210. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq. ) and have been assigned OMB Control Number 2120-0056. Alternative Methods of Compliance (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles ACO, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Los Angeles ACO. Special Flight Permits (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (f) The actions shall be done in accordance with Boeing Alert Service Bulletin DC9-27A362 (for Model DC-9 and Model MD-88 airplanes), dated February 11, 2000; Boeing Alert Service Bulletin MD90-27A034 (for Model MD-90-30 airplanes), dated February 11, 2000; and Boeing Alert Service Bulletin 717-27A0002 (for Model 717-200 airplanes), dated February 11, 2000. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on March 6, 2000, to all persons except those persons to whom it was made immediately effective by telegraphic AD 2000-03-51, issued on February 11, 2000, which contained the requirements of this amendment. Issued in Renton, Washington, on February 17, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00-4337 Filed 2-25-00; 8:45 am] BILLING CODE 4910-13-U