AIRWORTHINESS DIRECTIVE
CAA-AD-030/2001
Date of issue:
April 05, 2001
AIRCRAFT - ELEVATOR TAB - CONTROL SURFACES -
INSPECTION
Applicability:
Model 737-600, -700,
-700C, and -800 series airplanes, as listed in Boeing Alert Service Bulletin
737-55A1064, Revision 1, dated December 7, 2000; certificated in any
category.
Effective date: May 17, 2001
Compliance: Required as indicated in FAA AD 2001-06-15.
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
2001-06-15 BOEING: Amendment
39-12162. Docket 99-NM-312-AD.
Applicability: Model 737-600, -700, -700C, and -800
series airplanes, as listed in Boeing Alert Service Bulletin 737-55A1064,
Revision 1, dated December 7, 2000; 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 jamming, restricting, or binding of the
elevator control surfaces due to loose or missing fasteners; which could make
the movement of the elevator difficult and decrease aerodynamic control of the airplane;
accomplish the following:
Inspections of Fasteners, and Corrective Action, If
Necessary
(a) Within 250 flight hours or 30 days after the
effective date of this AD, whichever occurs first, perform a detailed visual
inspection of the fasteners in the elevator balance panel to detect inadequate
grip length, gaps between the bolt head, washer, and structure, and missing
fasteners, in accordance with paragraph 3.A. of the Accomplishment Instructions
of Boeing Service Bulletin 737-55A1064, Revision 1, dated December 7,
2000.
Note 2: Accomplishment of the actions specified in
Boeing Service Bulletin 737-55A1064, dated October 15, 1998, prior to the
effective date of this AD is acceptable for compliance with the applicable
actions required by this AD.
Note 3: 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."
(1) If adequate grip length is detected, if no gap is
detected, and if no fastener is missing, repeat the inspection thereafter at
intervals not to exceed 250 flight cycles until the requirements of paragraph
(b) of this AD have been accomplished; or prior to further flight, accomplish
the actions specified in paragraph (b) of this AD.
(2) If inadequate grip length is detected, if any gap
is detected, or if any fastener is missing, prior to further flight, accomplish
the actions specified in paragraph (b) of this AD.
Inspection and Corrective Actions, If Necessary
(b) Except as provided by paragraphs (a)(1) and (a)(2)
of this AD, within 3,000 flight cycles or 18 months after the first inspection
in accordance with paragraph (a) of this AD, whichever occurs first: Perform a
detailed visual inspection to detect missing fasteners at the locations
specified in Figure 2 of Boeing Service Bulletin 737-55A1064, Revision 1,
dated December 7, 2000, to detect inadequate grip length, and to determine
the locking torque of the nut plates specified in Figure 2 of the service
bulletin. These actions shall be done in accordance with paragraph 3.B.
("Fastener Inspection and Replacement") of the Accomplishment
Instructions of Boeing Service Bulletin 737-55A1064, Revision 1. Accomplishment
of the inspection constitutes terminating action for the repetitive inspection
requirements of paragraph (a)(1) of this AD.
(1) If no loose (i.e., minimum locking torque of nut
plate not achieved) fastener is detected, if no fastener is missing, and if
adequate grip length is found, no further action is required by this paragraph.
(2) If any fastener with an inadequate grip length is
found, prior to further flight, replace the fastener with a new fastener in
accordance with the service bulletin; and perform a detailed visual inspection
of adjacent elevator and horizontal stabilizer structure to detect damage. If
any damage is found on adjacent elevator or horizontal stabilizer structure,
prior to further flight, repair or replace the damaged structure or component in
accordance with the service bulletin.
(3) If any nut plate is found to have inadequate
locking torque, prior to further flight, install a new nut plate.
(4) If any fastener is missing, prior to further
flight, install a new fastener in accordance with the service bulletin; and
perform a detailed visual inspection of adjacent elevator and horizontal
stabilizer structure to detect damage. If any damage is found on adjacent
elevator or horizontal stabilizer structure, prior to further flight, repair or
replace the damaged structure or component in accordance with the service
bulletin.
(5) Where the service bulletin specifies to contact
Boeing for repair procedures or does not specify repair procedures, before
further flight, repair in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or in accordance with data
meeting the type certification basis of the airplane approved by a Boeing
Company Designated Engineering Representative 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 Manager’s approval
letter must specifically reference this AD.
Reporting Requirement
(c) Within 10 days after accomplishing any inspection
required by paragraphs (a) and (b)—not including paragraph (b)(2)—of this AD,
submit a report of the inspection results (positive findings only) to the
Manager, Seattle Manufacturing Inspection District Office, ANM-108S, 2500 East Valley
Road, Suite C-2, Renton, WA 98055-4056; fax (425) 227-1159. 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 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
(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.
Incorporation by Reference
(f) Except as provided by paragraph (b)(5) of this AD,
the actions shall be done in accordance with Boeing Service Bulletin 737-55A1064,
Revision 1, dated December 7, 2000. 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
(g) This amendment becomes effective on May 7, 2001.
FOR FURTHER INFORMATION CONTACT: Scott Fung, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 227-1221; fax (425) 227-1181.
Issued in Renton, Washington, on March 23, 2001.
Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.