AIRWORTHINESS DIRECTIVE

CAA-AD-T-036/2001

Date of issue: April 25, 2001

AIRCRAFT - ELEVATOR TAB - INSPECTION

Applicability: Model 737-600, -700, -700C, and -800 series airplanes, line numbers 1 through 788 inclusive, 790 through 814 inclusive, 816, 819, 821, and 823, certificated in any category.

Effective date: Upon receipt.

Compliance: Required as indicated in FAA AD 2001-09-51.

Remarks: The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel: 420 2 33320922, fax: 420 2 20562270.

Ing. Pavel MATOUŠEK

Director of Airworthiness Division

CAA CZ

EMERGENCY AIRWORTHINESS DIRECTIVE

2001-09-51 BOEING: Docket No. 2001-NM-126-AD.

Applicability: Model 737-600, -700, -700C, and -800 series airplanes, line numbers 1 through 788 inclusive, 790 through 814 inclusive, 816, 819, 821, and 823, 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.

Compliance: Required as indicated, unless accomplished previously.

To prevent excessive freeplay in the tab control mechanism, which could result in elevator tab flutter, and consequent loss of controllability of the airplane, accomplish the following:

(a) Within 10 days after receipt of this AD, inspect the small jam nut on the elevator tab control rods to detect inspection putty and to determine its condition, per paragraph III.B. of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1245, dated April 23, 2001.

(1) If inspection putty is found and it is intact, no further action is required by paragraph (a) of this AD.

(2) If inspection putty is missing or detached, prior to further flight, perform a torque check of the small and large jam nuts on the tab control rod, in accordance with paragraph III.B. of the alert service bulletin. Prior to further flight, perform corrective actions (including performing a detailed visual inspection of the threads on the rod end bearing for wear, measuring the diameter of the threads on the rod end bearing, replacing the rod end bearing and the threaded adjustment bushing, torquing the jam nuts, and applying inspection putty), as applicable, per paragraph III.B. of the alert service bulletin. If the tab control rod is disassembled and if no wear is found during accomplishment of the detailed visual inspection specified in this paragraph, measuring the diameter of the threads on the rod end bearing may be deferred until 250 flight cycles or 30 days after receipt of this AD, whichever occurs first.

NOTE 2: For the purposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required."

(b) For any control rod jam nut on which the putty was found and was intact, as specified in paragraph (a)(1) of this AD: Within 250 flight cycles or 30 days after receipt of this AD, whichever occurs first, perform a one-time inspection for torque of the small and large jam nuts on the tab control rods, per paragraph III.C. of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-27A1245, dated April 23, 2001. Prior to further flight, perform corrective actions (including performing a detailed visual inspection of the threads on the rod end bearing for wear, measuring the diameter of the threads on the rod end bearing, replacing the rod end bearing and the threaded adjustment bushing, torquing the jam nuts, and applying inspection putty), as applicable, per paragraph III.C. of the alert service bulletin.

(c) Within 15 days after accomplishing the inspections required by paragraphs (a) and (b) of this AD, submit a report of inspection findings, positive or negative, to Boeing per paragraph I.C. of the Planning Information of Boeing Alert Service Bulletin 737-27A1245, dated April 23, 2001.

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, Seattle 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, Seattle ACO.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.

(e) AD 2001-09-51, issued on April 24, 2001, becomes effective upon receipt.

For further information contact: Kenneth J. Fairhurst, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-1118; fax (425) 227-1181.

Issued in Renton, Washington, on April 24, 2001.

Original signed by:

Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.