[Federal Register Volume 67, Number 153 (Thursday, August 8, 2002)]
[Rules and Regulations]
[Pages 51459-51461]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-20019]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-75-AD; Amendment 39-12686; AD 2002-06-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300; A300 B4-600, B4-
600R, and F4-600R (Collectively Called A300-600); and A310 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to all Airbus Model A300; 
A300-600; and A310 series airplanes. That AD currently requires certain 
inspections of the airplane (including the vertical stabilizer, 
horizontal stabilizer, pylons, wing, and fuselage areas) following an 
in-flight incident resulting in extreme lateral loading. This document 
clarifies and corrects the information contact in the reporting 
requirement specified in paragraphs (b)(2) and (c)(2) of that AD. This 
correction is necessary to ensure that future reports are submitted to 
a specific point of contact.

DATES: Effective April 8, 2002.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, ANM-
116, International Branch, FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: On March 15, 2002, the Federal Aviation 
Administration (FAA) issued AD 2002-06-09, amendment 39-12686 (67 FR 
13259, March 22, 2002), which applies to all Airbus Model A300; A300-
600; and A310 series airplanes. That AD requires certain inspections of 
the airplane (including the vertical stabilizer, horizontal stabilizer, 
pylons, wing, and fuselage areas) following an in-flight incident 
resulting in extreme lateral loading. The actions required by that AD 
are intended to detect and correct reduced structural integrity of the 
airplane following any future event.

[[Page 51460]]

Need for the Correction

    Information obtained recently from Airbus Industrie indicates that 
a specific point of contact should be included for the reporting 
requirement submissions in that AD.
    The FAA has determined that a correction to AD 2002-06-09 is 
necessary. The correction will replace the reference to AI/SE-D32 
Technical Data and Documentation Services and the fax number for that 
office, as specified in paragraphs (b)(2) and (c)(2) of that AD, with 
the point of contact Jacques Leborgne and the fax number for that 
contact.

Correction of Publication

    This document corrects the error and correctly adds the AD as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13).
    The AD is reprinted in its entirety for the convenience of affected 
operators. The effective date of the AD remains April 8, 2002.
    Since this action only adds a point of contact, it has no adverse 
economic impact and imposes no additional burden on any person. 
Therefore, the FAA has determined that notice and public procedures are 
unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Correction

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Corrected]

    2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

2002-06-09  Airbus Industrie: Amendment 39-12686. Docket 2002-NM-75-
AD.

    Applicability: All Model A300; A300 B4-600, B4-600R, and F4-600R 
(collectively called A300-600); and A310 series airplanes; 
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 detect and correct reduced structural integrity of the 
airplane following an extreme lateral loading event, accomplish the 
following:

Lateral Load Factor Determination

    (a) As of the effective date of this AD, before further flight 
following an in-flight incident that results in extreme lateral 
loading, determine whether the lateral load factor (Ny) equaled or 
exceeded 0.3g. Extreme lateral loading can occur as a consequence of 
severe turbulence, loss of control of the aircraft involving yaw 
and/or roll maneuvers, hazardous systems failures, or other rare 
flight conditions. Then do the inspections specified in paragraph 
(b) or (c) of this AD, as applicable, at the time specified.

    Note 2: Acceptable methods for determining if the lateral load 
factor equaled or exceeded 0.3g include but are not limited to: 
Aircraft Communication Addressing and Reporting System (ACARS), 
Digital Flight Data Recorder (DFDR) readout, or Quick Access 
Recorder (QAR). A pilot report of extreme lateral acceleration in-
flight can be used to assess whether one of the previous methods 
should be used to determine the lateral load factor.


    Note 3: The inspections specified in paragraphs (b) and (c) of 
this AD are not necessary if lateral load factors exceed 0.3g when 
the airplane is on the ground (landing, taxiing).

Inspections for Certain Lateral Load Factors

    (b) For airplanes on which the lateral load factor (Ny) is 
greater than or equal to 0.3g, but less than 0.35g, accomplish the 
following actions:
    (1) Before further flight, do the detailed inspections specified 
in paragraph (d) of this AD.

Reporting Requirement

    (2) Within 5 days after accomplishing the inspections required 
by paragraph (b)(1) of this AD: Submit a report to Airbus, including 
the DFDR recording (or equivalent) of the portion of the flight when 
the extreme lateral loading event occurred, and other relevant 
information necessary to fully describe the event and develop the 
actual loads, including but not limited to, airplane weight, 
weather, and flight crew report. Submit a report of the inspection 
results (both positive and negative findings) to Jacques Leborgne, 
Airbus Industrie Customer Services Directorate, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex France; fax (+33) 5 61 93 36 14. 
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 4: Following accomplishment of the requirements of 
paragraphs (b)(1), (b)(2) and, if necessary, (e) of this AD, the 
airplane may be returned to service before accomplishing the 
inspections required by paragraph (b)(3) of this AD.

Supplementary Inspections

    (3) The manufacturer will develop an airplane loads assessment 
and recommend, if necessary, supplementary inspections of the 
applicable areas of the airplane (including the vertical stabilizer, 
horizontal stabilizer pylons, wing, and fuselage areas). Within 30 
days after the extreme lateral loading event, do the supplementary 
inspections of the airplane according to a method approved by the 
Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate.

    Note 5: The loads assessment, and if necessary, supplementary 
inspections required by paragraph (b)(3) of this AD, will be 
developed and proposed by the manufacturer based on the 
manufacturer's analysis of the report required by paragraph (b)(2) 
of this AD.

Inspections for Certain Other Lateral Load Factors

    (c) For airplanes on which the lateral load factor (Ny) is 
greater than or equal to 0.35g, accomplish the following:
    (1) Before further flight, do the detailed inspections specified 
in paragraph (d) of this AD.

Reporting Requirement

    (2) Before further flight after accomplishing the inspections 
required by paragraph (c)(1) of this AD: Submit a report to Airbus, 
including the DFDR recording (or equivalent) of the portion of the 
flight when the extreme lateral loading event occurred, and other 
relevant information necessary to fully describe the event and 
develop the actual loads, including but not limited to, airplane 
weight, weather, and flight crew report. Submit a report of the 
inspection results (both positive and negative findings) to Jacques 
Leborgne, Airbus Industrie Customer Services Directorate, 1 Rond 
Point Maurice Bellonte, 31707 Blagnac Cedex France; fax (+33) 5 61 
93 36 14. 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.

Supplementary Inspections

    (3) The manufacturer will develop an airplane loads assessment 
and recommend, if necessary, supplementary inspections of the 
applicable areas of the airplane (including the vertical stabilizer, 
horizontal stabilizer pylons, wing, and fuselage areas). Before 
further flight, do the supplementary inspections of the airplane 
according to a method approved by the Manager,

[[Page 51461]]

International Branch, ANM-116, FAA, Transport Airplane Directorate.

    Note 6: The loads assessment, and if necessary, supplementary 
inspections required by paragraph (c)(3) of this AD, will be 
developed and proposed by the manufacturer based on the 
manufacturer's analysis of the report required by paragraph (c)(2) 
of this AD.

Detailed Inspections

    (d) Do the following detailed inspections at the time specified 
in paragraph (b)(1) or (c)(1) of this AD, as applicable.
    (1) Do the inspections as specified in and per Chapter 05-51-17 
(Inspections After Flight in Excessive Turbulence or In Excess of 
VMO/MMO) of Airbus A300, A300-600 or A310 Airplane Maintenance 
Manual (AMM), as applicable. Extend the areas for these inspections 
as specified in paragraphs (d)(1)(i) and (d)(1)(ii) of this AD.
    (i) Extend the wing inspection area to include rib 22 through 
rib 29.
    (ii) Extend the fuselage inspection area from the inside to 
include frame 84 through 87 above stringer 23, and all areas of 
frame 91.
    (2) Do detailed inspections to find damage of the areas 
specified in paragraphs (d)(2)(i), (d)(2)(ii), and (d)(2)(iii) of 
this AD, according to a method approved by the Manager, 
International Branch, ANM-116.
    (i) Inspect the fuselage external surface under the vertical 
stabilizer to fuselage fairing, including side load fittings and 
lower surface of rib 1 of the vertical stabilizer.
    (ii) Inspect the rudder hinge arms and support fittings 1 
through 7, and the actuator support fittings of the vertical 
stabilizer.
    (iii) Inspect the rudder hinge fittings 1 through 7, and the 
actuator support fittings of the vertical stabilizer.

    Note 7: For the purposes of this AD, a detailed 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.''

Corrective Actions

    (e) If any damage is found during any inspection required by 
this AD: Before further flight, repair according to the method 
specified in the Airbus structural repair manual or according to a 
method approved by the Manager, International Branch, ANM-116, or by 
the Direction Generale de l'Aviation Civile or its delegated agent.

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, 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 8: 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

    (g) Special flight permits may be issued in accordance with 
Secs. 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

    (h) The effective date of this amendment remains April 8, 2002.

    Issued in Renton, Washington, on July 29, 2002.
Vi Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-20019 Filed 8-7-02; 8:45 am]
BILLING CODE 4910-13-P