AIRWORTHINESS
DIRECTIVE
CAA-AD-029/2002
Date of issue:
February 27, 2002
AIRCRAFT - MAIN LANDING GEAR - NUTS - REPLACEMENT
Applicability: Model 737-200,
-200C, -300, and -500 series airplanes; as identified in Boeing Service
Bulletin 737-57A1260, Revision 2, dated October 18, 2001; certificated in any
category.
Effective date: April 18, 2002
Compliance: Required as indicated in FAA
AD 2002-02-08.
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
2002-02-08 Boeing: Amendment 39-12636. Docket 2000-NM-332-AD.
Applicability: Model 737-200, -200C, -300, and
-500 series airplanes; as identified in Boeing Service Bulletin 737-57A1260,
Revision 2, dated October 18, 2001; certificated in any category.
Note 1: Operators should note that, if self-locking nuts are
installed on the support beam for the main landing gear (MLG) during
accomplishment of Boeing Service Bulletin 737-57-1216, dated December 17, 1992;
Revision 1, dated September 23, 1993; or Revision 2, dated May 6, 1999; the
airplane may be subject to the requirements of this AD.
Note 2: 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
(c) 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 the loosening
and loss of the support pin retaining bolt on the MLG, which could result in
the loosening and movement of the support pin, consequent cracked support
fittings, and collapse of the MLG, accomplish the following:
(a) Within 12 months
from the effective date of this AD, or within 1,500 flight cycles from the
effective date of this AD, whichever occurs first, replace the retaining bolt,
self-locking nut, and associated hardware of the support beam for the MLG with
a new bolt, castellated nut, and new hardware, per the Accomplishment
Instructions of Boeing Service Bulletin 737-57A1260, Revision 2, dated October
18, 2001.
Note 3: Replacements accomplished before the effective date
of this AD per Boeing Alert Service Bulletin 737-57A1260, dated June 15, 2000;
or Revision 1, dated October 12, 2000; are acceptable for compliance with
paragraph (a) of this AD.
(b) As shown under
paragraph 1.E., "Compliance," of Boeing Service Bulletin 737-57A1260,
Revision 2, dated October 18, 2001, if the airplane is in a configuration in
which a drilled shank bolt, castellated nut, and cotter pin are installed in
the subject areas of the support beam for the MLG, no action is necessary per
this AD.
(c) 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be obtained from
the Seattle ACO.
(d) Special flight
permits may be issued in accordance with Secs. 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.
(e) The actions shall be
done in accordance with Boeing Service Bulletin 737-57A1260, Revision 2, dated
October 18, 2001. 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
Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
(f) This amendment
becomes effective on March 19, 2002.
Issued in Renton,
Washington, on January 31, 2002.
[FR Doc. 02-2928 Filed 2-11-02;
8:45 am]