AIRWORTHINESS DIRECTIVE
CAA-AD-029/2001
Date of issue: April 05,
2001
AIRCRAFT - ELEVATOR TAB - INSPECTION/REPLACEMENT
Applicability:
Model 737-600, -700, and -800 series airplanes; line numbers 1 through 84
inclusive; certificated in any category.
Effective date: May 17, 2001
Compliance: Required
as indicated in FAA AD 2001-06-08.
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
2001-06-08 BOEING:
Amendment 39-12155. Docket 2001-NM-19-AD.
Applicability: Model 737-600, -700, and -800 series airplanes; line numbers 1
through 84 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 (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 detect and correct cracking of the elevator hinge
plates, which could lead to the loss of the attachment of the elevator to the
horizontal stabilizer, and consequent reduced controllability of the airplane,
accomplish the following:
Inspections and Corrective Actions
(a) Prior to the accumulation of 7,000 total flight
cycles or within 90 days after the effective date of this AD, whichever occurs
later, perform high frequency eddy current and detailed visual inspections of
the hinge plate at elevator hinge 4, and a detailed visual inspection of the
elevator hinge plate lugs (three locations) at elevator hinges 3, 5, 6, 7, and
8. Do these inspections per Part I of the Accomplishment Instructions of Boeing
Service Bulletin 737-55-1067, dated October 19, 2000. Repeat the
inspections thereafter no later than every 4,000 flight cycles, per the service
bulletin, until paragraph (b) of this AD has been accomplished. If any cracking
or unusual wear (i.e., elongated holes, loose or missing nuts or bolts, or
missing primer or finish) is found during any inspection per this paragraph,
before further flight, replace the affected hinge plate with a new, improved
hinge plate, and modify the elevator upper skin, the upper and lower hinge
covers, and the upper and lower closure panels, as applicable, per the service
bulletin, except as provided by paragraph (c) of this AD. Such replacement and
modification ends the repetitive inspections for the replaced hinge plate.
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."
Optional Replacement of Hinge Plates
(b) Replacement of the elevator hinge plates at hinges
3, 4, 5, 6, 7, and 8, with new, improved hinge plates; including modification
of the elevator upper skin, the upper and lower hinge covers, and the upper and
lower closure panels, as applicable; per Part II of the Accomplishment
Instructions of Boeing Service Bulletin 737-55-1067, dated October 19,
2000, except as provided by paragraph (c) of this AD; ends the repetitive
inspections required by this AD.
Exception to Service Bulletin Instructions: Wear
Limits
(c) During the replacement of elevator hinge plates
per paragraph (a) or (b) of this AD, where Boeing Service Bulletin 737-55-1067,
dated October 19, 2000, specifies to contact Boeing for wear limits,
before further flight, contact the Manager, Seattle Aircraft Certification
Office (ACO), FAA, or a Boeing Company Designated Engineering Representative
who has been authorized by the Manager, Seattle ACO, to make such findings. For
wear limits to be approved by the Manager, Seattle ACO, as required by this
paragraph, the Manager’s approval letter must specifically reference this AD.
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 3: 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 (c) of this AD,
the actions shall be done in accordance with Boeing Service Bulletin
737-55-1067, dated October 19, 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 April 9, 2001.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056;
telephone (425) 227-2028; fax (425) 227-1181.
Issued in Renton, Washington, on March 15, 2001.
Donald L. Riggin, Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.