AIRWORTHINESS
DIRECTIVE
CAA-AD-051/2002
Date of issue: 26. April 2002
AIRCRAFT - FUSELAGE STRUCTURE - NDT CHECK
Applicability: Model
737-200 and -200C airplanes having line numbers 1 through 291 inclusive,
certificated in any category.
Effective date: June 13, 2002
Compliance: Required as indicated in FAA AD 2002-07-11.
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
2002-07-11 Boeing: Amendment 39-12705. Docket 2000-NM-74-AD.
Applicability: Model 737-200 and -200C airplanes having line numbers 1
through 291 inclusive, 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 (f) 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 find and fix cracking of certain fuselage lap joint areas, which could
result in rapid decompression of the airplane, accomplish the following:
Repetitive Low Frequency Eddy Current (LFEC) Inspections
(a) Do an LFEC inspection to find cracking of the left and right stringers S-10
and S-14 lap joints of the fuselage, located between body station (BS) 727 and
BS 747, per Figures 7 and 8 of the Accomplishment Instructions of Boeing
Service Bulletin 737-53A1177, Revision 6, dated May 31, 2001; at the time
specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. Repeat the
inspection after that at intervals not to exceed 1,200 flight cycles until
accomplishment of the lap joint modification (repair) required by paragraph (e)
of this AD.
(1) For airplanes that have accumulated 70,000 or more total flight cycles as
of the effective date of this AD: At the later of the times specified in
paragraphs (a)(1)(i) and (a)(1)(ii) of this AD.
(i) Before the accumulation of 71,200 total flight cycles.
(ii) Within 300 flight cycles after the effective date of this AD.
(2) For airplanes that have accumulated 45,000 or more total flight cycles, but
less than 70,000 total flight cycles as of the effective date of this AD: At
the later of the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this
AD.
(i) Before the accumulation of 50,000 total flight cycles.
(ii) Within 1,200 flight cycles after the effective date of this AD.
Crack Repair
(b) Except as provided by paragraph (c) of this AD: If any cracking is found
during any inspection required by this AD, before further flight, repair per
Part II ("Crack Repair") of the Accomplishment Instructions of Boeing
Service Bulletin 737-53A1177, Revision 6, dated May 31, 2001.
(c) If any cracking is found during any inspection required by this AD, and
Boeing Service Bulletin 737-53A1177, Revision 6, dated May 31, 2001, specifies
to contact Boeing for repair instructions: Repair before further flight, per a
method approved by the Manager, Seattle Aircraft Certification Office (ACO),
FAA; or per data meeting the type certification basis of the airplane approved
by a Boeing Company Designated Engineering Representative (DER) who has been
authorized by the Manager, Seattle ACO, to make such findings. For a repair
method to be approved by the Manager, Seattle ACO, as required by this
paragraph, the approval letter must specifically reference this AD.
Compliance Plan
(d) For airplanes on which the modification required by paragraph (e) of this
AD has not been done as of the effective date of this AD: Within 3 months after
the effective date of this AD, submit a plan to the FAA identifying a schedule
for compliance with paragraph (e) of this AD. This schedule must include, for
each of the operator's affected airplanes, the estimated dates when the
required actions will be accomplished. For the purposes of this paragraph,
"FAA" means the Principal Maintenance Inspector (PMI) for operators
that are assigned a PMI, or the cognizant Flight Standards District Office for
other operators. 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.
Note 2: Operators are not required to submit revisions to the compliance
plan required by paragraph (d) of this AD to the FAA.
Lap Joint Modification (Repair)
(e) Except as provided by paragraph (d) of this AD, before the accumulation of
50,000 total flight cycles or within 5,000 flight cycles after the effective
date of this AD, whichever comes later: Install the lap joint repair of the
left and right stringer S-10 and S-14 lap joints of the fuselage, between body
station (BS) 727 and BS 747, per Part III ("Lap Joint Repair") of the
Accomplishment Instructions, or Part 1.E.3. "Compliance," of Boeing
Service Bulletin 737-53A1177, Revision 6, dated May 31, 2001, as applicable.
Installation of this repair ends the repetitive inspections of the repaired
areas required by paragraph (a) of this AD.
Note 3: Installation of the lap joint repair before the effective date
of this AD per Boeing Service Bulletin 737-53A1177, Revision 4, dated September
2, 1999; or Revision 5, dated February 15, 2001; is acceptable for compliance
with paragraph (e) of this AD.
Alternative Methods of Compliance
(f) 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 ACO. 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.
Special Flight Permits
(g) 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
(h) Except as provided by paragraphs (c) and (d) of this AD, the actions shall
be done in accordance with Boeing Service Bulletin 737-53A1177, Revision 6,
dated May 31, 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.
Effective Date
(i) This amendment becomes effective on May 17, 2002.