[Federal Register Volume 67, Number 122 (Tuesday, June 25, 2002)]
[Proposed Rules]
[Pages 42739-42741]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-15912]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 67, No. 122 / Tuesday, June 25, 2002 / 
Proposed Rules  

[[Page 42739]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-297-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; and Model A300 B4-601, B4-603, B4-620, B4-605R, B4-622R, and 
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 a previously proposed airworthiness 
directive (AD) applicable to certain Airbus Model A300 B2 and B4 series 
airplanes and Model A300 B4-601, B4-603, B4-620, B4-605R, B4-622R, and 
F4-605R airplanes. The previously proposed AD would have revised an 
existing AD to remove one model from the applicability. That AD 
currently requires a one-time inspection for cracking of the gantry 
lower flanges in the main landing gear (MLG) bay area; and repair, if 
necessary. This new action, which proposes to supersede the existing 
AD, would remove the one model from the applicability. For certain 
airplanes, it would retain the one-time inspection for cracking of the 
gantry lower flanges and repair, if necessary. For other airplanes, 
this new action would add repetitive inspections of the gantry lower 
flanges; repair, if necessary; and reinforcement of the left-hand and 
right-hand gantry. The actions specified by this new proposed AD are 
intended to detect and correct cracking of the gantry lower flanges in 
the MLG bay area, which could result in decompression of the airplane.

DATES: Comments must be received by July 30, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-297-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. 2000-NM-297-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: Gary Lium, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1112; 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 Number 2000-NM-297-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 No. 2000-NM-297-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 
Airbus Model A300 B2 and B4 series airplanes; and Model A300 B4-601, 
B4-603, B4-620, B4-605R, B4-622R, and F4-605R airplanes, was published 
as a notice of proposed rulemaking (NPRM) in the Federal Register on 
January 10, 2001 (66 FR 1917). That NPRM proposed to revise AD 98-13-
37, amendment 39-10628 (63 FR 34589, June 25, 1998), which is 
applicable to certain Airbus Model A300 and all Model A300-600 series 
airplanes. (See the ``Explanation of Airplane Model Designation'' 
below.) The NPRM proposed to continue to require a one-time inspection 
for cracking of the gantry lower flanges in the main landing gear (MLG) 
bay area, and repair, if necessary, but would have removed Model A300 
F4-622R airplanes from the applicability. Removing Model A300 F4-622R 
airplanes from the proposed applicability was based on information 
received from the Direction G[eacute]n[eacute]rale de l'Aviation Civile 
(DGAC), the French civil airworthiness authority. This

[[Page 42740]]

information indicated that Model A300 F4-622R airplanes are not subject 
to cracking of the gantry lower flanges in the MLG bay area.

Explanation of Airplane Model Designation

    The applicability of AD 98-13-37 includes the following airplane 
models: A300 B4-601, B4-603, B4-620, B4-605R, B4-622R, F4-605R, and F4-
622R. However, since these airplanes are commonly referred to as 
``Model A300-600 series airplanes,'' that model designation was 
specified in the applicability of that AD. Since the issuance of that 
AD, the FAA has determined that these airplanes should be designated 
exactly as they appear on the type certificate data sheet. Therefore, 
the applicability of the previously proposed AD, as well as that of 
this new NPRM, designates each specific model (excluding Model F4-622R 
airplanes, which are purposely removed) without referring to the common 
name of the airplane.

Actions Since Issuance of Previous Proposal

    Since the issuance of the previous proposal, the FAA has been 
advised that Airbus has issued Service Bulletin A300-53-6128, dated 
March 5, 2001, for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, 
B4-622R, and F4-605R airplanes. The service bulletin describes 
procedures for repetitive inspections for cracks of the lower flanges 
of gantries 3, 4, and 5 on the left-hand and right-hand sides; repair 
of any cracks detected; and reinforcement of the left-hand and right-
hand gantries. The service bulletin also provides a sequence of steps 
for accomplishing threshold and repetitive inspections, repair, and 
reinforcement in the Synoptic Chart included as Figure 2, Sheets 1 
through 5; the Synoptic Chart also indicates the interval between 
certain steps.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although the service bulletin specifies 
that the manufacturer may be contacted for disposition of certain 
repairs, this proposal would require those repairs to be accomplished 
per a method approved by the FAA.

FAA's Determination

    The FAA has determined that--for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, B4-622R, and F4-605R airplanes--the following 
actions must be accomplished in accordance with Airbus Service Bulletin 
A300-53-6128, dated March 5, 2001:
     Initial and repetitive inspections for cracking of the 
gantry lower flanges in the main landing gear bay area.
     Repairs, if necessary.
     Reinforcement of the left-hand and right-hand gantries.

Conclusion

    Since these requirements expand the scope of the originally 
proposed rule, the FAA has determined that it is necessary to issue 
this supplemental notice of proposed rulemaking which proposes to 
supersede the existing AD rather than to revise it. Issuance of this 
supplemental NPRM provides opportunity for public comment on the 
proposed repetitive inspections.

Cost Impact

One-Time Inspection

    The number of airplanes affected by AD 98-13-37 was estimated to be 
67. The one-time inspection required by that AD was estimated to take 
approximately 4 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of AD 98-13-37 on U.S. operators was estimated to be $16,080, or 
$240 per airplane.
    The FAA currently estimates that 43 Model A300 B2 and B4 series 
airplanes of U.S. registry would be affected by the one-time inspection 
required by AD 98-13-37 and proposed to be retained in this 
supplemental NPRM. We also estimate that all affected U.S. operators 
have previously accomplished these requirements, so that the future 
cost impact of this requirement is minimal.

Repetitive Inspections

    The FAA estimates that 78 Model A300 B4-601, B4-603, B4-605R, B4-
620, B4-622R, and F4-605R airplanes of U.S. registry would be affected 
by the proposed repetitive inspections, that it would take 
approximately 12 work hours per airplane to accomplish each inspection, 
and that the average labor rate is $60 per work hour. Based on these 
figures, the cost impact of the proposed repetitive inspections on 
those U.S. operators is estimated to be $56,160, or $720 per airplane, 
per inspection cycle.
    The cost impact figures for the repetitive inspections are based on 
assumptions that no operator has yet accomplished those repetitive 
inspections and that no operator would accomplish those repetitive 
inspections in the future if this proposed 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 39-10628 (63 FR 
34589, June 25, 1998) and by adding a new airworthiness directive to 
read as follows:

Airbus: Docket 2000-NM-297-AD. Supersedes AD 98-13-37, Amendment 39-
10628.

    Applicability: Model A300 B2 and B4 series airplanes on which 
Airbus

[[Page 42741]]

Modification 3474 has been accomplished; and Model A300 B4-601, B4-
603, B4-605R, B4-620, B4-622R, and F4-605R airplanes on which Airbus 
Modification 12169 has not been incorporated in production; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (c) 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 cracking of the gantry lower flanges in 
the main landing gear (MLG) bay area, which could result in 
decompression of the airplane, accomplish the following:

One-Time Inspection and Corrective Action, if Needed

    (a) For Model A300 B2 and B4 series airplanes: Prior to the 
accumulation of 16,300 total flight cycles, or within 500 flight 
cycles after July 30, 1998 (the effective date of AD 98-13-37, 
amendment 39-10628), whichever occurs later, perform a one-time 
ultrasonic inspection for cracking of the gantry lower flanges in 
the MLG bay area, in accordance with Airbus All Operators Telex 
(AOT) 53-11, dated October 13, 1997.
    (1) If any cracking is detected, prior to further flight, repair 
in accordance with the AOT.
    (2) If no cracking is detected, no further action is required by 
this AD.

Repetitive Inspections and Corrective Action, if Needed

    (b) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622R, and 
F4-605R airplanes: Perform the requirements of paragraphs (b)(1) and 
(b)(2) of this AD, in accordance with Airbus Service Bulletin A300-
53-6128, dated March 5, 2001.
    (1) Perform initial and repetitive ultrasonic inspections or 
high-frequency eddy current (HFEC) inspections for cracks of the 
lower flanges of gantries 3, 4, and 5 between fuselage frames FR47 
and FR54, in accordance with the thresholds and the Accomplishment 
Instructions, including the Synoptic Chart contained in Figure 2, 
sheets 1 through 5 inclusive, of the service bulletin.
    (2) Perform repairs and reinforcements, in accordance with the 
thresholds and the Accomplishment Instructions, including the 
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, 
of the service bulletin, except as specified in paragraph (b)(3) of 
this AD.
    (3) If a new crack is found during any inspection required by 
paragraph (b)(1) or (b)(2) of this AD and the Synoptic Chart 
contained in Figure 2, sheets 1 through 5 inclusive, of the service 
bulletin specifies to contact Airbus for appropriate action: Prior 
to further flight, repair per a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate.

Alternative Methods of Compliance

    (c) 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

    (d) 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directives 1997-372-236(B) R2, dated April 18, 2001, 
and 2001-091(B), dated March 21, 2001.


    Issued in Renton, Washington, on June 18, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-15912 Filed 6-24-02; 8:45 am]
BILLING CODE 4910-13-P