-Caveat Lector-
Here is more information about the FAA
"Airworthiness Directives" in June 2, 2000
which ordered airlines to inspect the vertical
stabilizers on the type Airbus which crashed in
New York last Monday. They knew as long ago as
May 2000 that these Airbusses had a serious structural
defect. Now they are pretending they don't have a
clue as to why Flight 587 crashed.
The FAA inspections were ordered "To prevent failure
of the bonds of the vertical stabilizer spar box to
the skin, which could lead to reduced structural
integrity."
The FAA explained its Airworworthiness Directive...
"was prompted by reports received from the Direction
Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, of localized
failure of bonds of the spars and stringers on several
vertical stabilizer spar boxes to the skin. The
failure resulted from contamination of the bonding
surface during the production process. The
requirements of that AD are intended to detect and
correct disbonding of the vertical stabilizer
structure, which could result in reduced structural
integrity of the spar boxes of the vertical
stabilizer.
Airbus Service Bulletin A320-55A1027, dated May 13,
2000; Revision 01, dated August 1, 2000; or Revision
02, dated February 13, 2001: Prior to or concurrent
with the ultrasonic inspection required by paragraph
(a) of this AD, modify the vertical stabilizer to
ensure proper reinforcement of the structure/skin
attachments, in accordance with Airbus Service
Bulletin A320-55-1026, Revision 01, dated May 20,
1999.
New Requirements of Proposed AD
Repetitive Inspections and Repair, If Necessary
(c) Within 1,100 flight cycles from the previous
inspection performed in accordance with paragraph (a)
of this AD, or 60 days after the effective date of
this AD, whichever occurs later: Perform an ultrasonic
inspection to detect disbonding of the skin attachment
at the spars and the stringers of the vertical
stabilizer spar box, in accordance with Airbus Service
Bulletin A320-55A1027, dated May 13, 2000; Revision
01, dated August 1, 2000; or Revision 02, dated
February 13, 2001.
(d) If no damage is detected, or if only a single area
of damage is found and it is less than or equal to an
area of 300 square millimeters (mm\2\) during any
ultrasonic inspection required by this AD, repeat the
ultrasonic inspection thereafter at intervals not to
exceed 1,100 flight cycles.
(e) If any damage is detected and the area of damage
found is greater than 300 mm\2\, or if multiple damage
is found on one specific component (stringer/spar
attachment) during any ultrasonic inspection required
by this AD, prior to further flight, accomplish
applicable repairs in accordance with Airbus Service
Bulletin A320-
55A1027, dated May 13, 2000; Revision 01, dated August
1, 2000; or 02, dated February 13, 2001. Repeat the
ultrasonic inspection thereafter at intervals not to
exceed 1,100 flight cycles.
Modification
(f) Within 5 years after the date of manufacture of
the airplane: Install fasteners to reinforce the
attachment between the skin panel and areas of the
vertical stabilizer affected by disbonding, in
accordance with Airbus Service Bulletin A320-55-1028,
Revision 03, dated November 2, 2000. Accomplishment of
the installation terminates the repetitive inspections
required by paragraph (c) of this AD.
Alternative Methods of Compliance
(g)(1) 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, International Branch, ANM-116, FAA,
Transport Airplane Directorate. Operators shall submit
their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then
send it to the Manager, International Branch, ANM-116.
(2) Alternative methods of compliance, approved
previously in accordance with AD 2000-11-27, amendment
39-11776, are approved as alternative methods of
compliance with paragraphs (a) and (b) of this AD.
Note 2: Information concerning the existence of
approved alternative methods of compliance with this
AD, if any, may be obtained from the International
Branch, ANM-116.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NM-413-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319, A320, and
A321 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the supersedure of an
existing airworthiness directive (AD), applicable to
certain Airbus Model A319, A320, and A321 series
airplanes, that currently requires a one-time
ultrasonic inspection to detect disbonding of the skin
attachments at the stringers and spars of the vertical
stabilizer, and repair, if necessary. For certain
airplanes, that AD also requires prior or concurrent
modification of the vertical stabilizer to ensure
proper reinforcement of its attachment to the skin.
This action would require ultrasonic inspections of
the subject area, and repair, as necessary. It would
also require installation of fasteners to reinforce
the bonds to the skin, which would terminate the
repetitive inspections. This proposal is prompted by
issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness
authority. The actions specified by the proposed AD
are necessary to prevent failure of the bonds of the
vertical stabilizer spar boxes to the skin, which
could lead to reduced structural integrity of the spar
boxes.
Nakano
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