[Federal Register Volume 66, Number 223 (Monday, November 19, 2001)]
[Proposed Rules]
[Pages 57896-57900]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-28794]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-322-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600 and A300 B4-
600R Series Airplanes, and Model A300 F4-605R Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to all Airbus Model A300 B4-600, A300 B4-
600R, and A300 F4-600R series airplanes, that would have superseded an 
existing AD. The existing AD requires repetitive inspections to detect 
cracks of certain attachment holes, installation of new fasteners, and 
follow-on inspections or repair if necessary. The proposed AD would 
have reduced the inspection threshold and repetitive intervals and 
expanded the area to be inspected. This supplemental notice of proposed 
rulemaking (NPRM) would further expand the area to be inspected, and 
would require a modification of the angle fittings of frame FR47. This

[[Page 57897]]

supplemental NPRM would also remove certain airplanes from the 
applicability. The actions specified by this supplemental NPRM are 
intended to prevent fatigue cracking of the forward fitting of fuselage 
frame FR47, which could result in reduced structural integrity of the 
frame.

DATES: Comments must be received by December 14, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-322-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 99-NM-322-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket 99-NM-322-AD.'' The postcard will be date-stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket 99-NM-322-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to all 
Airbus Model A300 B4-600, A300 B4-600R, and A300 F4-600R series 
airplanes, was published as a notice of proposed rulemaking (NPRM) in 
the Federal Register on July 20, 2000 (65 FR 44991). That original NPRM 
proposed to supersede AD 97-16-06, amendment 39-10097 (62 FR 41257, 
August 1, 1997), which is applicable to all Airbus Model A300 B4-600, 
A300 B4-600R, and A300 F4-600R series airplanes. A correction to AD 97-
16-06 was published in the Federal Register on August 25, 1997 (62 FR 
44888). The original NPRM proposed to continue to require repetitive 
inspections to detect cracks of certain attachment holes, installation 
of new fasteners, and follow-on inspections or repair if necessary. The 
original NPRM would have reduced the inspection threshold and 
repetitive intervals and expanded the area to be inspected. The 
original NPRM was prompted by reports of cracking in the internal angle 
fittings of the wing center box at fuselage frame FR47 on airplanes 
that had not reached the inspection threshold required by AD 97-16-06, 
and cracking around certain fastener holes that were not required to be 
inspected by AD 97-16-06. Such fatigue cracking, if not corrected, 
could result in reduced structural integrity of the frame.

Actions Since Issuance of Original NPRM

    Since the issuance of the original NPRM, the FAA has been advised 
by the Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, of recent inspection results that 
warrant a revision of the existing inspection program for certain areas 
of fuselage frame FR47. Specifically, an investigation of new crack 
findings indicates the need for an inspection of additional holes 
(holes A, B, C, D, E, F, G, P, Q, and S) of the baseplate/horizontal 
section of the angle fittings of the wingbox. The investigation further 
revealed fatigue sensitivity of additional holes (holes Y, U, V, W, and 
X) of the angle web fitting on airplanes on which a particular 
modification had not been correctly embodied in production.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A300-57-6049, Revision 4, dated 
July 27, 2000, which describes procedures for repetitive rotating probe 
inspections to detect cracking of holes in the left and right internal 
angles of the wing center box. Corrective actions include reaming, 
drilling, drill-stopping holes, chamfering, follow-on inspections, and 
installing new or oversize fasteners. The original version of this 
service bulletin was cited as the appropriate source of service 
information for the inspections required by AD 97-16-06. Revision 3 was 
described in the original NPRM and cited as the appropriate source of 
service information for the proposed inspections. Revision 4 includes 
minor procedural changes not included in Revision 3, and includes 
procedures for the inspection of additional holes (holes Y, U, V, W, 
and X) on certain airplanes.
    Airbus has also issued Service Bulletin A300-57-6086, dated June 6, 
2000, which describes procedures for repetitive rotating probe 
inspections to detect cracking of ten holes (holes A, B, C, D, E, F, G, 
P, Q, and S) in the horizontal flange of the internal corner angle 
fitting at frame FR47. For crack repair, this service bulletin provides 
corrective actions that include inspecting hole T if any cracking is 
found around hole G, reaming the holes, and installing oversize 
fasteners.

[[Page 57898]]

    Airbus has also issued Service Bulletin A300-57-6050, Revision 02, 
dated February 10, 2000, which describes procedures for a modification 
of the angle fittings at frame FR47, which involves performing a 
rotating probe inspection to detect cracking of fasteners holes most 
sensitive to fatigue, cold expanding the holes, and installing new 
medium interference fitting bolts. The modification is intended to 
improve the fatigue life of the subject area.
    Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition. The 
DGAC classified these service bulletins as mandatory and issued French 
airworthiness directive 2000-533-328(B), dated December 27, 2000, to 
ensure the continued airworthiness of these airplanes in France.

Comments

    Due consideration has been given to comments received in response 
to the original NPRM.

Request To Remove Certain Airplanes From Applicability

    One commenter requests that Model A300 F4-622R airplanes be removed 
from the applicability of the original NPRM to correspond to the 
revised French airworthiness directive, which was issued specifically 
to exclude those airplanes.
    The FAA concurs. Model A300 F4-622R airplanes are not subject to 
the identified unsafe condition. The applicability of this supplemental 
NPRM has been revised to remove those airplanes.

Request To Revise Compliance Times

    Several commenters request that the grace periods for inspection of 
holes H, I, K, L, M, and N, as specified in the original NPRM, be 
revised to correspond to the grace periods specified in Airbus Service 
Bulletin A300-57-6049. The commenters state that the grace periods 
provided in the service bulletin are intended to allow operators to 
properly plan the required work, and will ensure safety via a longer 
grace period for newer airplanes and a shorter grace period for older 
airplanes. One commenter, an operator, states that its newest airplanes 
would be subject to out-of-sequence inspections and potential 
modifications, at significant cost to the operator. The operator 
contends that the grace periods provided in the service bulletin would 
provide an ``equivalent level of safety.''
    The FAA concurs, for the reasons provided by the commenters. 
Paragraphs (a) and (b) of this supplemental NPRM refer to the 
compliance thresholds and repetitive intervals specified in paragraph 
1.A.(2), Planning Information, of the service bulletin.

Request To Remove Restriction on Flight With Cracks

    One commenter requests that the original NPRM be revised to remove 
the exception to Service Bulletin A300-57-6049 regarding flight with 
cracks. The original NPRM had included a provision that would prohibit 
further flight with cracking detected in the attachment holes. The 
commenter states that the service bulletin does not allow flight with a 
free crack but rather recommends corrective action to eliminate the 
crack immediately or repair it temporarily until it can be eliminated.
    The FAA partially concurs. In the section titled ``Differences 
Between the Proposed Rule and Relevant Service Information,'' the 
original NPRM incorrectly interpreted the service bulletin as allowing 
flight with cracks, in contrast to FAA policy. The service bulletin 
does provide for temporary repair with follow-up repetitive 
inspections, but specifies that, for certain conditions, operators must 
contact the manufacturer for further instructions prior to further 
flight. The original NPRM specified that corrective actions be 
performed in accordance with the service bulletin. To clarify the 
requirements for repair, this supplemental NPRM specifies that repair 
of cracking be done by ``applicable corrective actions'' in accordance 
with the service bulletin.

Conclusion

    Since these changes expand the scope of the original NPRM, the FAA 
has determined that it is necessary to reopen the comment period to 
provide additional opportunity for public comment.

Explanation of Proposed Requirements of This Supplemental NPRM

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, this supplemental NPRM would require 
accomplishment of the actions specified in the service bulletins 
described in this supplemental NPRM, except as discussed below.

Differences Between This Supplemental NPRM and the Service 
Bulletins

    Operators should note that, although the service bulletins specify 
that the manufacturer may be contacted for disposition of certain 
repair conditions, this supplemental NPRM would require the repair of 
those conditions to be accomplished in accordance with a method 
approved by either the FAA or the DGAC (or its delegated agent). In 
light of the type of repair that would be required to address the 
identified unsafe condition, and in consonance with existing bilateral 
airworthiness agreements, the FAA has determined that, for this 
supplemental NPRM, a repair approved by either the FAA or the DGAC 
would be acceptable for compliance with this supplemental NPRM.
    Furthermore, Airbus Service Bulletins A300-57-6049 and A300-57-6086 
specify that operators need not count touch-and-go landings in 
determining the total number of landings between consecutive 
inspections, when those landings represent less than five percent of 
the landings between inspection intervals. However, fatigue cracking, 
which was found on the forward fitting of fuselage frame FR47 at the 
level of the last fastener of the external angle fitting, is aggravated 
by landing. Therefore, the FAA has determined that all touch-and-go 
landings must be counted in determining the total number of flight 
cycles between two consecutive inspections.

Cost Impact

    The FAA estimates that 74 airplanes of U.S. registry would be 
affected by this proposed AD. The average labor rate is $60 per work 
hour. The FAA provides the following cost estimates for the actions 
proposed by this supplemental NPRM:

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                Action                        Work hours               Parts cost           Per-airplane cost
----------------------------------------------------------------------------------------------------------------
Inspection per paragraph (a).........  7 or 13 (depending on    $0.....................  $420 or $780, per
                                        configuration).                                   inspection.
Inspection per paragraph (b).........  30.....................  6,637 or 19,091,         8,437 or 20,891, per
                                                                 depending on kit         inspection.
                                                                 required.
Modification per paragraph (c).......  65 to 365..............  3,370..................  7,270 to 25,270.
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[[Page 57899]]

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 39-10097 (62 FR 
41257, August 1, 1997), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 99-NM-322-AD. Supersedes AD 97-16-06, 
Amendment 39-10097.

    Applicability: All Model A300 B4-600 and A300 B4-600R series 
airplanes and all Model A300 F4-605R 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)(1) 
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 fatigue cracking of the forward fitting of fuselage 
frame FR47, which could result in reduced structural integrity of 
the frame, accomplish the following:

Inspections

    (a) Perform a rotating probe inspection to detect cracking of 
the applicable attachment holes on the left and right internal 
angles of the wing center box, in accordance with Airbus Service 
Bulletin A300-57-6049, Revision 4, dated July 27, 2000. Do the 
inspection at the applicable time specified by paragraph 1.A.(2), 
Planning Information, of the service bulletin, except as required by 
paragraph (e) of this AD. Repeat the inspection thereafter at 
intervals not to exceed the applicable interval specified in the 
service bulletin, except that all touch-and-go landings must be 
counted in determining the total number of flight cycles between 
consecutive inspections.
    (1) If no cracking is found: Prior to further flight, install 
new fasteners in accordance with the service bulletin.
    (2) If any cracking is found: Prior to further flight, perform 
applicable corrective actions (including reaming, drilling, drill-
stopping holes, chamfering, follow-on inspections, and installing 
new or oversize fasteners) in accordance with the service bulletin, 
except as required by paragraph (d) of this AD.
    (b) Perform a rotating probe inspection to detect cracking of 
the applicable attachment holes in the horizontal flange of the 
internal corner angle fitting of frame FR47, in accordance with 
Airbus Service Bulletin A300-57-6086, dated June 6, 2000. Do the 
inspection at the applicable time specified by the service bulletin, 
except as required by paragraph (e) of this AD. Repeat the 
inspection thereafter at intervals not to exceed the applicable 
interval specified in the service bulletin, except that all touch-
and-go landings must be counted in determining the total number of 
flight cycles between consecutive inspections.
    (1) If no cracking is detected: Prior to further flight, install 
new fasteners in accordance with the service bulletin.
    (2) If any cracking is detected: Prior to further flight, 
perform applicable corrective actions (including inspecting hole T, 
reaming the holes, and installing oversize fasteners) in accordance 
with the service bulletin, except as required by paragraph (d) of 
this AD.

Modification

    (c) Modify the left and right internal angle fittings of the 
wing center box. The modification includes performing a rotating 
probe inspection to detect cracking, repairing cracks, cold 
expanding holes, and installing medium interference fitting bolts. 
Perform the modification in accordance with and at the applicable 
time specified by paragraph 1.B.(4), Accomplishment Timescale, of 
Airbus Service Bulletin A300-57-6050, Revision 02, dated February 
10, 2000; except as required by paragraphs (d) and (e) of this AD.

    Note 2: Modification prior to the effective date of this AD in 
accordance with Airbus Service Bulletin A300-57-6050, dated 
September 9, 1994, or Revision 01, dated May 31, 1999, is acceptable 
for compliance with the requirements of paragraph (c) of this AD.

Exception to Specifications in Service Bulletins

    (d) If any crack is detected during any inspection required by 
paragraph (a), (b), or (c) of this AD, and the applicable service 
bulletin specifies to contact the manufacturer for disposition of 
certain corrective actions: Prior to further flight, repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
or the Direction Generale de l'Aviation Civile (DGAC) (or its 
delegated agent).
    (e) Where the service bulletins specified in paragraphs (a), 
(b), and (c) of this AD specify a grace period relative to receipt 
of the service bulletin, this AD requires compliance within the 
grace period following the effective date of this AD, if the 
threshold has been exceeded.

Alternative Methods of Compliance

    (f)(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. 
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 97-16-06, amendment 39-10097, are not considered 
to be approved as alternative methods of compliance with any 
requirements of this AD.

    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.


[[Page 57900]]



Special Flight Permits

    (g) 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.

    Note 4: The subject of this AD is addressed in French 
airworthiness directive 2000-533-328(B), dated December 27, 2000.


    Issued in Renton, Washington, on November 9, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-28794 Filed 11-16-01; 8:45 am]
BILLING CODE 4910-13-U