AD 2000-16-07

[Federal Register Volume 65, Number 159 (Wednesday, August 16, 2000)]
[Rules and Regulations]
[Pages 49897-49899]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-20506]



[[Page 49897]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-184-AD; Amendment 39-11862; AD 2000-16-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Industrie Model A300 B2 and B4 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Industrie Model A300 B2 and B4 
series airplanes, that currently requires inspection of the fuselage 
longitudinal lap joints and circumferential joints, and of the 
stringers and doublers for bonding delamination and cracks; and 
repairs, as necessary. This amendment requires expansions of certain 
inspection areas; revisions of certain inspection thresholds or 
intervals; changes in references to inspection methods; and the 
addition of a modification to certain longitudinal lap joints. This 
amendment is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by this AD are intended to prevent delamination and cracking 
of the fuselage, which could result in rapid decompression of the 
airplane.

DATES: Effective September 20, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 20, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 85-07-09, 
amendment 39-5033 (50 FR 13548, April 5, 1985), which is applicable to 
certain Airbus Industrie Model A300 B2 and B4 series airplanes, was 
published in the Federal Register on June 1, 2000 (65 FR 34993). The 
action proposed to continue to require inspection of the fuselage 
longitudinal lap joints and circumferential joints, and of the 
stringers and doublers for bonding delamination and cracks; and 
repairs, as necessary. The action also proposed to require expansions 
of certain inspection areas; revisions of certain inspection thresholds 
or intervals; changes in references to inspection; and the addition of 
a modification to certain longitudinal lap joints.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 20 airplanes of U.S. registry that will be 
affected by this AD.
    The inspection of the bonded longitudinal lap joints and 
circumferential joints to detect bonding delamination that is currently 
required by AD 85-07-09, and retained in this AD, takes approximately 
146 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of this 
currently required action on U.S. operators is estimated to be 
$175,200, or $8,760 per airplane, per inspection cycle.
    The inspection of the bonded longitudinal lap joints and 
circumferential joints to detect corrosion and cracking that is 
currently required by AD 85-07-09, and retained in this AD, takes 
approximately 72 work hours per airplane to accomplish. Based on these 
figures, the cost impact of this currently required action on U.S. 
operators is estimated to be $86,400, or $4,320 per airplane, per 
inspection cycle.
    The inspections of the bonded stringers and doublers to detect 
debonding that are currently required by AD 85-07-09, and retained in 
this AD, take approximately 129 work hours per airplane to accomplish. 
Based on these figures, the cost impact of these currently required 
actions on U.S. operators is estimated to be $154,800, or $7,740 per 
airplane, per inspection cycle.
    The modification of the bonded longitudinal lap joint required by 
this AD will take as much as 581 work hours (not including access and 
close) per airplane to accomplish, at an average labor rate of $60 per 
work hour. Required parts will cost as much as $16,148 per airplane, 
depending on kits purchased. Based on these figures, the cost impact of 
the required modification on U.S. operators is estimated to be as high 
as $1,020,160, or $51,008 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD, and that no operator would accomplish those actions in the future 
if this AD were not adopted. The cost impact figures discussed in AD 
rulemaking actions represent only the time necessary to perform the 
specific actions actually required by the AD. These figures typically 
do not include incidental costs, such as the time required to gain 
access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 49898]]

Adoption of the Amendment

    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  [Amended]

    2. Section 39.13 is amended by removing amendment 39-5033 (50 FR 
13548, April 5, 1985), and by adding a new airworthiness directive 
(AD), amendment 39-11862, to read as follows:

2000-16-07 Airbus Industrie: Amendment 39-11862. Docket 97-NM-184-
AD. Supersedes AD 85-07-09, Amendment 39-5033.

    Applicability: Model A300 B2 and B4 series airplanes, 
manufacturer serial numbers 003 through 156 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 (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 prevent rapid decompression of the airplane due to bonding 
delamination and cracking of the fuselage, accomplish the following:

Restatement of Requirements of AD 85-07-09

Delamination Inspections of Longitudinal Lap and Circumferential 
Joints

    (a) Except as required by paragraph (d) of this AD: Prior to the 
threshold limits specified in Table 1 of Airbus Service Bulletin 
A300-53-148, Revision 6, dated October 10, 1984, or within 6 months 
after May 13, 1985 (the effective date of AD 85-07-09), whichever 
occurs later, inspect the fuselage longitudinal lap joints and 
circumferential joints for bonding delamination, in accordance with 
the service bulletin.
    (1) If no delamination is detected, repeat these inspections in 
accordance with the schedule shown in Table 1 of the service 
bulletin.
    (2) If delamination is detected during any inspection, prior to 
further flight, perform the actions indicated in Figure 3, ``Follow-
up Action,'' of the service bulletin.

Corrosion and Crack Inspections of Longitudinal Lap and 
Circumferential Joints

    (b) Except as required by paragraph (d) of this AD: Prior to the 
threshold limits specified in Figure 1, ``Inspection Program,'' of 
Airbus Service Bulletin A300-53-178, Revision 4, dated October 10, 
1984, or within 6 months after May 13, 1985, whichever occurs later, 
visually inspect for corrosion and cracks, and repair if necessary, 
the bonded longitudinal lap joints and circumferential joints 
specified in Figure 1 of the service bulletin, in accordance with 
the service bulletin. Repeat the inspections thereafter in 
accordance with the schedule shown in Figure 1 of the service 
bulletin.

Delamination Inspections of Stringers and Doublers

    (c) Except as required by paragraph (d) of this AD: Prior to the 
threshold limits specified in Figure 1, ``Inspection Frequency,'' of 
Airbus Service Bulletin A300-53-149, Revision 6, dated October 10, 
1984, or within 6 months after May 13, 1985, whichever occurs later, 
inspect for debonding, and repair, if necessary, bonded stringers 
and bonded doublers in the area between frame 1 and frame 18 and 
between frame 40 and frame 80 on all airplanes up to and including 
serial number 156, and in the area between frame 18 and frame 40 on 
all airplanes up to and including serial number 104. Repeat the 
inspections thereafter at intervals specified in Figure 1 of the 
service bulletin, except for repaired areas. The inspections of 
stringers are divided into three areas, as indicated in Figure 2 of 
the service bulletin, with the following options:
    (1) Inspection in Area 1 is not required if Modification No. 
2904, described in Airbus Service Bulletin A300-53-146, dated 
November 28, 1980, has been incorporated.
    (2) Preventive riveting of stringers located in Area 2 in 
accordance with Airbus Service Bulletin A300-53-197, dated October 
10, 1984, allows for an extension of the interval of subsequent 
repetitive inspections to the interval required for Area 3.

New Requirements of This AD

Later Service Bulletin Revisions

    (d) After the effective date of this new AD, only the following 
service bulletin revisions shall be used for compliance thresholds 
and intervals and for accomplishment instructions for the actions 
required by this AD, as specified in paragraphs (d)(1), (d)(2), and 
(d)(3) of this AD. For any airplane that, as of the effective date 
of this AD, has exceeded a revised threshold or interval for any 
specified action, accomplish that action within 6 months after the 
effective date of this AD.
    (1) Airbus Service Bulletin A300-53-148, Revision 11, dated 
September 8, 1998, shall be used for the requirements of paragraph 
(a) of this AD. For corrective actions and follow-on inspections, 
Figure 5, ``Follow-up Action,'' of the service bulletin shall be 
used.
    (2) Airbus Service Bulletin A300-53-178, Revision 10, dated 
September 8, 1998, shall be used for the requirements of paragraph 
(b) of this AD. For inspection thresholds and intervals, Paragraph 
C., ``Description,'' of the service bulletin shall be used.
    (3) Airbus Service Bulletin A300-53-149, Revision 14, including 
Appendix 01, dated September 8, 1998, shall be used for the 
requirements of paragraph (c) of this AD. For inspection thresholds 
and intervals, Figure 1, Sheet 1, ``Inspection Frequency,'' of the 
service bulletin shall be used.

Modification of Lap Joints (Partial Terminating Action)

    (e) Within 60 months after the effective date of this AD, modify 
the bonded longitudinal lap joints in accordance with Airbus Service 
Bulletin A300-53-0209, Revision 10, dated July 5, 1999. 
Accomplishment of the modification terminates the repetitive 
inspections required by paragraph (a) of this AD for stringers 29 
and 35 in section 18 only.

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, 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.

    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.

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.

Incorporation by Reference

    (h) Except as provided by paragraphs (a), (b), and (c) of this 
AD, the actions shall be done in accordance with Airbus Service 
Bulletin A300-53-148, Revision 11, dated September 8, 1998; Airbus 
Service Bulletin A300-53-178, Revision 10, dated September 8, 1998; 
Airbus Service Bulletin A300-53-0149, Revision 14, including 
Appendix 01, dated September 8, 1998; and Airbus Service Bulletin 
A300-53-0209, Revision 10, dated July 5, 1999; as applicable. 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 Airbus Industrie, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France. 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directives 97-371-

[[Page 49899]]

235(B), dated December 3, 1997, and 1984-140-064(B)R3, dated October 
6, 1999.

Effective Date

    (i) This amendment becomes effective on September 20, 2000.

    Issued in Renton, Washington, on August 8, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-20506 Filed 8-15-00; 8:45 am]
BILLING CODE 4910-13-U