[Federal Register Volume 67, Number 106 (Monday, June 3, 2002)]
[Rules and Regulations]
[Pages 38193-38195]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-13422]



 ========================================================================
 Rules and Regulations
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains regulatory documents 
 having general applicability and legal effect, most of which are keyed 
 to and codified in the Code of Federal Regulations, which is published 
 under 50 titles pursuant to 44 U.S.C. 1510.
 
 The Code of Federal Regulations is sold by the Superintendent of Documents. 
 Prices of new books are listed in the first FEDERAL REGISTER issue of each 
 week.
 
 ========================================================================
 

  Federal Register / Vol. 67, No. 106 / Monday, June 3, 2002 / Rules 
and Regulations  

[[Page 38193]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-322-AD; Amendment 39-12765; AD 2002-11-04]
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: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all Airbus Model A300 B4-600, A300 B4-600R, and 
A300 F4-600R series airplanes (A300-600), that currently requires an 
inspection to detect cracks of certain attachment holes; and 
installation of new fasteners and follow-on inspections or repair if 
necessary. This amendment requires repetitive inspections to detect 
cracks of certain attachment holes, installation of new fasteners, 
follow-on inspections or repair if necessary, and modification of the 
angle fittings of frame FR47. This amendment revises the applicability 
of the existing AD. The actions specified by this AD 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: Effective July 8, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 8, 2002.

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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 97-16-06, 
amendment 39-10097 (62 FR 44888, August 25, 1997), which is applicable 
to all Airbus Model A300 B4-600, A300 B4-600R, and A300 F4-600R series 
airplanes (A300-600), was published as a supplemental notice of 
proposed rulemaking (NPRM) in the Federal Register on November 19, 2001 
(66 FR 57896). The supplemental NPRM proposed to require repetitive 
inspections to detect cracks of certain attachment holes, installation 
of new fasteners, follow-on inspections or repair if necessary, and 
modification of the angle fittings of frame FR47.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received from the single commenter on the supplemental 
NPRM. The commenter generally supports the proposal.

Request To Allow Use of Alternative Fasteners

    The commenter requests that the supplemental NPRM be revised to 
approve the use of alternative fasteners listed in the Airbus A300 
Structural Repair Manual (SRM), Chapter 51-40-32 (``Fastener 
Alternative--Metallic Structure''). This would relieve operators of 
initiating, and the FAA of approving, requests for alternative methods 
of compliance to use fasteners not specified by the AD.
    We do not concur with this request. Airbus Service Bulletin A300-
57-6049, Revision 4, dated July 27, 2000, is cited in paragraph (a) of 
the supplemental NPRM (and this final rule) as the appropriate source 
of service information for the rotating probe inspection of the 
internal angles of the wing center box. In consonance with the parallel 
French airworthiness directive, this AD requires operators to follow 
the specifications of that service bulletin. SRM Chapter 51-40-32 is 
not listed as a reference in the service bulletin; therefore, this AD 
does not provide credit for the use of fasteners identified in that SRM 
chapter. However, under the provisions of paragraph (f)(1) of this 
final rule, as the commenter suggests, the FAA may approve requests to 
use alternative fasteners if data are submitted to substantiate that 
such alternative fasteners would provide an acceptable level of safety.
    Operators should note that SRM Chapter 51-40-31, which is listed as 
a reference in Service Bulletin A300-57-6049, does allow different, 
oversized fasteners to be installed, which will provide operators some 
additional flexibility in accomplishing the requirements of this AD. 
Because SRM Chapter 51-40-31 is cited in the service bulletin, use of 
the fasteners identified in that chapter is implicitly allowed by this 
AD; therefore, no change to the final rule is necessary in this regard.

Coordination of Global Review

    The commenter suggests that the FAA, Airbus, and the DGAC perform a 
global review of other areas of the A300-600 wing box area that are 
also subject to the inspection requirements of existing ADs. According 
to the commenter, reviewing the whole box section, instead of 
concentrating on one area at a time, may enhance safety of flight.
    We recognize the potential value of a global approach in addressing 
multiple inspections of the same general area, and we will take the 
commenter's suggestion under advisement. However, in this case the 
identified unsafe condition is a more immediate concern that should be 
addressed in a unique AD. Coordinating a global review of related ADs 
would further delay issuance of this AD, which, in any event, is not 
the proper forum to address such a review. No change to the final rule 
is necessary in this regard.

Request To Revise Compliance Times

    The commenter requests that a single threshold/interval be 
established for all of the inspections of the wing center

[[Page 38194]]

section currently required by different ADs. These ADs have different 
inspection thresholds, and the required actions are labor-intensive. 
Coinciding compliance times would greatly reduce the downtime that 
would be required if the actions of each AD are performed separately.
    We do not concur with the request. The compliance times and 
requirements of each related AD are based on the manufacturer's case-
by-case analysis of each individual structural condition. Operators are 
responsible for scheduling the actions required for each applicable AD. 
No change to the final rule is necessary in this regard.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Interim Action

    This is considered to be interim action. The manufacturer is 
currently developing procedures for an inspection of the repaired and 
reinforced area on those airplanes on which the actions of Service 
Bulletin A300-57-6069 have been accomplished. If the FAA finds these 
actions appropriate to address the unsafe condition identified by this 
AD, the FAA may consider further rulemaking once these inspection 
procedures are developed, approved, and available.

Cost Impact

    The FAA estimates that 74 airplanes of U.S. registry will be 
affected by this AD. The average labor rate is $60 per work hour. The 
FAA provides cost estimates for the actions specified by this AD, as 
follows:

----------------------------------------------------------------------------------------------------------------
                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.
----------------------------------------------------------------------------------------------------------------

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the 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 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.

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.

[sect] 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-10097 (62 FR 
44888, August 25, 1997) and by adding a new airworthiness directive 
(AD), amendment 39-12765, to read as follows:

2002-11-04 Airbus Industrie: Amendment 39-12765. 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, performing follow-on inspections, and 
installing new or oversize

[[Page 38195]]

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.

Exceptions to Specifications in Service Bulletins

    (d) If any crack is detected during any inspection required by 
paragraph (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 
applicable 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 approved as 
alternative methods of compliance with the applicable 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.

Special Flight Permits

    (g) Special flight permits may be issued in accordance with 
[sect][sect] 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 required by paragraph (d) of this AD: The actions 
shall be done in accordance with Airbus Service Bulletin A300-57-
6049, Revision 4, dated July 27, 2000; Airbus Service Bulletin A300-
57-6086, dated June 6, 2000; and Airbus Service Bulletin A300-57-
6050, Revision 02, dated February 10, 2000; as applicable. Revision 
02 of Airbus Service Bulletin A300-57-6050 contains the following 
effective pages:

------------------------------------------------------------------------
                                Revision level
         Page number            shown on page      Date shown on page
------------------------------------------------------------------------
1, 4, 8, 9, 17-32, 41, 42,     02.............  February 10, 2000.
 57, 58, 61-63, 75, 77.
2, 3, 5-7, 10-12, 33, 34, 37,  01.............  May 31, 1999.
 38, 47, 59, 60, 76.
13-16, 35, 36, 39, 40, 43-46,  Original.......  September 9, 1994.
 48-56, 64-74.
------------------------------------------------------------------------

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

Effective Date

    (i) This amendment becomes effective on July 8, 2002.


    Issued in Renton, Washington, on May 22, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-13422 Filed 5-31-02; 8:45 am]
BILLING CODE 4910-13-P