AD 2001-07-10 Airworthiness Directives; McDonnell Douglas Model DC-9-81, -82, -83, and -87 Series Airplanes, Model MD-88 Airplanes, and Model MD-90-30 Series Airplanes

Models named: As listed in DC-9-81, -83, -87 series. Read the applicability below — it usually turns on serial or part numbers too.

Models identified in Table 1 of this AD, certificated in any category; excluding those airplanes on which the modification specified in the applicable service bulletin listed in Table 1 of this AD has been done. Table 1 is as follows: Table 1.—Applicability Model As listed in DC-9-81, -83, and -87 series airplanes, and MD-88 airplanes Boeing Alert Service Bulletin MD80-27A359, Revision 01, dated March 26, 2001. MD-90-30 series airplanes Boeing Alert Service Bulletin MD90-27A031, Revision 01, dated March 26, 2001. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 the flightcrew from performing a scheduled landing on a runway of potentially insufficient length due to failure of the weight-on-wheels spoiler lockout mechanism system and possible inactivation of the autospoiler actuator, which could result in the airplane overrunning the end of the runway during landing on a wet or icy runway, accomplish the following: Airplane Flight Manual Revisions (a) For Model DC-9-81, -82, -83, and -87 series airplanes, and MD-88 airplanes: Within 48 clock hours after the effective date of this AD, revise the Performance Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be done by inserting a copy of this AD in the AFM. “ In-flight Spoiler Lockout Mechanism Installed and Activated, and Automatic Ground Spoiler System Operated. When the in-flight spoiler lockout mechanism is installed and activated, the wet or icy runway landing field length, which is determined from the appropriate Landing Field Length and Speed Chart, must be increased by 1,720 feet under either of the following conditions: a. The weight-on-wheels unlocking feature is not installed; or b. The weight-on-wheels unlocking feature is installed, but inoperative. When the in-flight spoiler lockout mechanism is deactivated, the above landing field length is not required.” (b) For Model MD-90-30 series airplanes: Within 48 clock hours after the effective date of this AD, revise the Performance Section of the FAA-approved AFM to include the following statement. This may be done by inserting a copy of this AD in the AFM. “ Landing Field Length for A Wet or Icy Runway. Increase landing field length, which is determined from the Basic Manual, by 1,800 feet (549 meters) for a wet or icy runway with 28-degree and 40-degree flaps. There is no landing field length penalty for a dry runway. In-flight spoiler lockout mechanism may NOT be deactivated, as indicated in the Master Minimum Equipment List (MMEL).” Note 2: The MD-90 MMEL, system and sequence number 65-02, and the second proviso of system and sequence number 65-03, specifies currently that, for 10 days, the in-flight spoiler lockout mechanism system may be deactivated. Where differences exist between the current specification of the MMEL and the requirements of this AFM limitation, the AFM limitation prevails. Optional Terminating Modifications (c) Accomplishment of the actions specified in paragraphs (c)(1) and (c)(2) of this AD, per the applicable Boeing service bulletin identified in Table 2 of this AD, constitutes terminating action for the AFM revision requirements of paragraph (a) or (b) of this AD, as applicable. After doing those actions, the AFM revision required by paragraph (a) or (b) of this AD, as applicable, may be removed from the AFM. Table 2 is as follows: Table 2.—Applicable Service Bulletins Alert service bulletin Revision level Date Model MD80-27A359 Original or 01 January 29, 2001, March 26, 2001 DC-9-81, -82, -83, and -87 series airplanes, and MD-88 airplanes. MD90-27A031 Original or 01 January 29, 2001, March 26, 2001 MD-90-30 series airplanes. (1) Install the spoiler support bracket assemblies and relays; and (2) Revise the spoiler lockout relay wiring. 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 Aircraft Certification Office (ACO), FAA. 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the 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. Effective Date (f) This amendment becomes effective on April 27, 2001. Issued in Renton, Washington, on April 5, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-9019 Filed 4-11-01; 8:45 am] BILLING CODE 4910-13-U