AD 2002-08-05 Airworthiness Directives; Bombardier Model DHC-8-400, -401, and -402 Series Airplanes

Models named: DHC-8-400, -401, -402 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DHC-8-400, -401, and -402 series airplanes; serial numbers 4001 and subsequent; 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 ensure that the flight crew has the procedures necessary to address failure of the main landing gears (MLG) to extend following a gear-down selection; and to detect and correct such failure, which could result in a gear-up landing and possible injury to passengers and crew; accomplish the following: Revision of FAA-Approved Airplane Flight Manual (AFM) (a) Within 3 days after the effective date of this AD, amend all copies of the FAA-approved Bombardier Series 400 AFM, PSM 1-84-1A (for Models 400, 401, and 402), by adding the following procedure to the Limitations section of the AFM, and opposite page 4-21-1 of the AFM; and advise all flight crew members of these changes; (the revision may be accomplished by inserting a copy of this AD into the Limitations section of the AFM and affected paragraphs of the AFM): “If ONE main landing gear fails to extend after performing landing gear extension per normal procedures given in paragraph 4.3.7 and alternate extension procedures per paragraph 4.21.1 of the AFM: 1. Visually confirm that the affected gear has not extended and that the associated doors have opened. 2. Ensure No. 2 hydraulic system pressure and quantity are normal and the following landing gear advisory lights are illuminated: selector lever amber, gear green locked down (nose and non-affected main gear), red gear unlocked (affected main gear) and all amber doors open. 3. NOSE L/G RELEASE handle—Return to the stowed position. 4. LANDING GEAR ALTERNATE EXTENSION door—Close fully. 5. MAIN L/G RELEASE handle—Return to the stowed position. 6. LANDING GEAR ALTERNATE RELEASE door—Close fully. 7. LANDING GEAR lever—DN. 8. L/G DOWN SELECT INHIBIT SW—Normal and guarded. Check amber doors open advisory lights out (nose and non-affected main gear) and LDG GEAR INOP caution light out. 9. LANDING GEAR lever—UP Check all gear, door and LANDING GEAR lever advisory lights out. 10. With minimum delay, LANDING GEAR lever—DN. Check 3 green gear locked down advisory lights illuminate, all amber doors open, red gear unlocked and selector lever amber advisory lights out. 11. Items 9 and 10 may be repeated in an effort to achieve 3 gear down and locked. CAUTION Should the LDG GEAR INOP caution light illuminate, or loss of no. 2 hydraulic system pressure or quantity, or any abnormality in landing gear system indication other than those associated with the affected main landing gear be experienced, see paragraph 4.21.1 ALTERNATE LANDING GEAR EXTENSION.” Replacement of Uplock Assembly (b) At the later of the times specified in paragraph (b)(1) or (b)(2) of this AD: Replace the left and right MLG uplock assemblies, part number (P/N) 46500-3, with new uplock assemblies, P/N 46500-3, per Chapter 32-31-21, dated January 5, 2001, of Bombardier Series 400 Aircraft Maintenance Manual, PSM 1-84-2. Do the replacement thereafter at intervals not to exceed 2,500 flight hours or 3,000 flight cycles, whichever occurs earlier. (1) Before the accumulation of 2,500 total flight hours or 3,000 total flight cycles, whichever occurs earlier; or (2) Within 14 days after the effective date of this AD. Note 2: Bombardier DHC-8 Alert Service Bulletin A84-32-15, dated February 4, 2002, references Chapter 32-11-01, dated January 5, 2001, of Bombardier Series 400 AMM, PSM 1-84-2, as an additional source of service information for procedures to replace an MLG uplock roller. One-Time Inspection of MLG Uplock Rollers (c) Within 30 days after the effective date of this AD, inspect the left and right MLG uplock rollers for the presence of an inner low friction (black-colored) liner, per the Accomplishment Instructions of Bombardier DHC-8 Alert Service Bulletin A84-32-15, dated February 4, 2002; and, before further flight, do the actions required by paragraph (c)(1) or (c)(2) of this AD. Corrective Actions (1) If a low friction liner is present, reinstall the existing uplock roller; or install a new uplock roller, P/N 46575-1, having a low friction liner; on the shock strut of the MLG; per the alert service bulletin. (2) If a low friction liner is NOT present, replace the existing uplock roller with a new uplock roller, P/N 46575-1, having a low friction liner, on the shock strut of the MLG; per the alert service bulletin. 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, New York 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, New York ACO. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. Special Flight Permits (e) Special flight permits may be issued in accordance with §§ 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 inspection of the uplock rollers and corrective actions shall be done per Bombardier DHC-8 Alert Service Bulletin A84-32-15, dated February 4, 2002. (The manufacturer's name is listed only on the first page of the document; no other page contains this information.) 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 Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 4: The subject of this AD is addressed in Canadian airworthiness directive CF-2002-13, dated February 4, 2002. Effective Date (g) This amendment becomes effective on April 23, 2002. Issued in Renton, Washington, on April 11, 2002. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 02-9391 Filed 4-17-02; 8:45 am] BILLING CODE 4910-13-U