U.S. Department of Transportation
Federal Aviation Administration
Aircraft Certification Service
Emergency Airworthiness Directive
Transmitted as follows is emergency airworthiness directive (AD) 2001-23-51, for the attention of certain owners and operators of Airbus Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes.
Background
On November 12, 2001, an Airbus Model A300 B4-605R airplane was involved in an accident shortly after takeoff from John F. Kennedy International Airport, Jamaica, New York.The cause of the accident is under investigation by the National Transportation Safety Board (NTSB).Although the NTSB has not determined the cause of the accident, it has determined that the vertical stabilizer departed the airplane.In addition, the rudder was found separated from the vertical stabilizer.
The vertical stabilizer on Airbus Model A300-600 series airplanes with Airbus Modification 4886 is manufactured of advanced composite materials.The vertical stabilizer on Airbus Model A310 series airplanes with the same modification is manufactured of the same materials.Failure of the vertical stabilizer-to-fuselage attachment fittings, transverse (side) load fittings, or rudder-to-vertical stabilizer attachment fittings, if not corrected, could result in loss of the vertical stabilizer and/or rudder and consequent loss of control of the airplane.
The
FAA considers that, before structural failure, it may be possible to detect
indications of possible failure modes that could result in separation of
the vertical stabilizer from the airplane.These
indications include edge delaminations, cracked paint, surface distortions,
other surface damage, and failure of the transverse (side) load fittings.Similarly,
indications of failure of the rudder assembly, which could lead to failure
of the vertical stabilizer, may also be detectable with such an inspection.Although
neither the FAA nor the NTSB have reached conclusions with respect to these
possible failures on the accident airplane, we consider it prudent to require
an inspection of these structures to identify any such indication that
may exist.
These airplane models are
manufactured in France and are type-certificated for operation in the United
States under the provisions of section 21.29 of the Federal Aviation Regulations
(14 CFR 21.29) and the applicable bilateral airworthiness agreement.The
FAA has coordinated this action with the Direction Generale de l'Aviation
Civile (DGAC), which is the airworthiness authority for France, and the
DGAC has taken similar action.
Explanation of the Requirements of the Rule
Interim Action
This is considered to be interim
action.The inspection report that
is required by this AD will enable the FAA, DGAC, and manufacturer to obtain
better insight into the potential unsafe condition, and eventually to develop
final action to address it, if necessary.If
final action is identified, the FAA may consider further rulemaking.
Determination of Rule’s Effective Date
Since a situation exists that
requires the immediate adoption of this regulation, it is found that notice
and opportunity for prior public comment hereon are impracticable, and
that good cause exists for making this AD effective in less than 15 days.
This rule is issued under 49 U.S.C. Section 44701 (formerly section 601 of the Federal Aviation Act of 1958) pursuant to the authority delegated to me by the Administrator, and is effective immediately upon receipt of this AD.
AD 2001-23-51 AIRBUS INDUSTRIE:Docket No. 2001-NM-359-AD.
Applicability:Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes; certificated in any category; having a vertical stabilizer made of composite material (reference Airbus Modification 4886).
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
(e) of this AD.The request should
include an assessment of the effect of the modification, alteration, or
repair on the potential unsafe condition addressed by this AD; and, if
the potential unsafe condition has not been eliminated, the request should
include specific proposed actions to address it.
Compliance:Required as indicated, unless accomplished within the last 6 months.
To prevent failure of the
vertical stabilizer-to-fuselage attachment fittings or transverse (side)
load fittings, or rudder-to-vertical stabilizer attachment fittings, which
could result in loss of the vertical stabilizer and/or rudder and consequent
loss of control of the airplane, accomplish the following:
Compliance Time
(a)Within 15 days after
the receipt of this AD, do the inspections specified in paragraphs (b)
and (c) of this AD.
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.”
Inspection and Corrective Actions
(b)Perform a one-time detailed visual inspection to detect repairs and alterations to, and damage of the vertical stabilizer attachment fittings, including the main attachment lugs and the transverse (side) load fittings. Any alteration made to the composite structures, either during production or post-production, is considered areas of primary concern.Gain access to the vertical stabilizer attachment fittings by removing external fairings and internal access covers and inspect both sides of affected attachment fittings.Damage of the metallic areas includes pulled or loose fasteners, wear areas, distorted flanges, cracks, and corrosion.Damage of the composite areas includes delamination; distorted surfaces that may indicate delamination; cracks or abrading in the paint surface; surface damage; evidence of moisture damage; and cracked, splitting, or frayed fibers.
(1)If any damage is found to the vertical stabilizer attachment fittings, including the main attachment lugs and the transverse (side) load fittings, before further flight, repair per a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate.
(2)If any repair or alteration to the attachment lug areas of the vertical stabilizer has been accomplished previously, before further flight, the repair or alteration must be approved by the Manager, International Branch, ANM-116.
(c)Perform
a one-time detailed visual inspection to detect damage of the rudder hinge
fittings, hinge arms, and support fittings for all rudder hinges, and rudder
actuator support fittings. Damage
of the metallic areas includes pulled or loose fasteners, wear areas, distorted
flanges, cracks, and corrosion.Damage
of the composite areas includes delamination; distorted surfaces that may
indicate delamination; cracks or abrading in the paint surface; surface
damage; evidence of moisture damage; and cracked, splitting, or frayed
fibers.If any damage is found, before
further flight, repair per the manufacturer’s structural repair manual,
or per a method approved by the Manager, International Branch, ANM-116.
Report
(d)Submit a report of inspection findings (both positive and negative) to the Manager, International Branch, ANM-116; fax (425) 227-1149; at the applicable time specified in paragraph (d)(1) or (d)(2) of this AD.The report must include the inspection results, a description of any repair, alteration, or discrepancy found, including digital photographs of the damaged area, the airplane serial number, and the number of flight cycles and flight hours on the airplane.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.
(1)For airplanes on which the inspection is accomplished after receipt of this AD:Submit the report within 5 days after performing the inspection required by paragraph (a) of this AD.
(2)For
airplanes on which the inspection has been accomplished prior to receipt
of this AD:Submit the report within
5 days after receipt of this AD.
Alternative Methods of Compliance
(e)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.Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, which may add comments and then send it to the Manager, International Branch, ANM-116.
Note 3:Information
concerning the existence of approved alternative methods of compliance
with this AD, if any, may be obtained from the International Branch, ANM-116.
Special Flight Permits
(f)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.
Effective Date
(g)AD 2001-23-51, issued on November 16, 2001, becomes effective upon receipt.
For further information contact:Henry Offermann, Aerospace Engineer; Airframe and Cabin Safety Branch, ANM-115, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; telephone (425) 227-2676; fax (425) 227-1100.
Issued
in Washington, DC, on November 16, 2001.
John J. Hickey,
Director,
Aircraft Certification Service