AD 2002-07-05 - Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-600, and A30...

Type	Manufacturer	Model	Details
aircraft	Airbus	A300 B2	Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R Series Airplanes; and Model A300 F4-605R Airplanes

Unsafe Condition

Cracking of certain fittings due to local stress concentrations at the upper flange runout of frame 40, which could result in reduced structural integrity of the airplane.

AI-generated summary from the source AD text. Verify against the official source before acting.

Required Actions

Conduct repetitive inspections for cracking of certain fittings. Take corrective action if necessary. For certain airplanes, install a modification. Optional terminating action is available for the repetitive inspections.

AI-generated summary from the source AD text. Verify against the official source before acting.

Compliance Time

Before further flight

AI-generated summary from the source AD text. Verify against the official source before acting.

Affected Aircraft

Airbus Model A300 B2, A300 B4, A300 B4-600, A300 B4-600R series airplanes, and Model A300 F4-605R airplanes.

AI-generated summary from the source AD text. Verify against the official source before acting.

Federal Register Abstract

This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R series airplanes, and Model A300 F4-605R airplanes. This AD requires repetitive inspections for cracking of certain fittings, corrective action if necessary, and, for certain airplanes, a modification. This AD also provides an optional terminating action for the repetitive inspections. The actions specified by this AD are intended to detect and correct propagation of cracks on the frame 40 aft fittings due to local stress concentrations at the upper flange runout of frame 40, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.

Document Text

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[Federal Register Volume 67, Number 68 (Tuesday, April 9, 2002)]
[Rules and Regulations]
[Pages 16983-16987]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-8278]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-86-AD; Amendment 39-12699; AD 2002-07-05]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2, A300 B4, 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 adopts a new airworthiness directive (AD),
applicable to all Airbus Model A300 B2, A300 B4, A300 B4-600, and A300
B4-600R series airplanes, and Model A300 F4-605R airplanes. This AD
requires repetitive inspections for cracking of certain fittings,
corrective action if necessary, and, for certain airplanes, a
modification. This AD also provides an optional terminating action for
the repetitive inspections. The actions specified by this AD are
intended to detect and correct propagation of cracks on the frame 40
aft fittings due to local stress concentrations at the upper flange
runout of frame 40, which could result in reduced structural integrity
of the airplane. This action is intended to address the identified
unsafe condition.

DATES: Effective May 14, 2002.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 14, 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) to include an airworthiness
directive (AD) that is applicable to all Airbus Model A300 B2, A300 B4,
A300 B4-600, and A300 B4-600R series airplanes; and Model A300 F4-605R
airplanes; was published as a supplemental notice of proposed
rulemaking (NPRM) in the Federal Register on January 4, 2002 (67 FR
530). That action proposed to require repetitive inspections for
cracking of certain fittings, corrective action if necessary, and, for
certain airplanes, a modification; and would have provided for optional
terminating action for the repetitive inspections.

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 a single commenter in response to the second
supplemental NPRM.

Provide Credit for Prior Inspection and Refer to Terminating Action

One commenter asks the FAA to revise the proposed rule to provide
credit for an inspection already performed in accordance with the
original issue of Airbus Service Bulletin A300-53-6048, dated January
16, 1996, provided that the inspection is accomplished in conjunction
with Airbus Service Bulletin A300-57-6053. The commenter states that
this would make the proposed rule consistent with the original issue of
the corresponding French airworthiness directive, 98-481-270(B), dated
December 2, 1998.
The same commenter also requests that we revise the proposed rule
to provide for optional terminating action on Model A300 B4-600 and
A300 B4-600R series airplanes and Model A300 F4-605R airplanes. The
commenter states that inspection and rework per

[[Page 16984]]

Airbus Service Bulletins A300-57-6052 and A300-57-6053 constitutes
terminating action for airplanes on which no cracks are found and no
subsequent rework is required.
The FAA concurs with the intent of the commenter's request, but we
have already accommodated the request previously. We added Note 2 to
the first supplemental NPRM to provide credit for an inspection done in
accordance with the original issue of Airbus Service Bulletin A300-53-
6048. In addition, we revised paragraph (b)(8) and paragraph (e) in the
first supplemental NPRM to clarify that modification per Airbus Service
Bulletin A300-57-6053, Revision 1, dated October 31, 1995, or Revision
02, dated June 2, 1999, terminates the proposed requirements,
regardless of the inspection results. No change to the final rule is
necessary.

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 as proposed in the second
supplemental NPRM.

Cost Impact

The FAA estimates that 70 Model A300 B2, A300 B4, A300 B4-600, and
A300 B4-600R series airplanes; and Model A300 F4-605R airplanes; of
U.S. registry will be affected by this AD.
For affected airplanes, it will take approximately 92 work hours
per airplane to accomplish the required modification, at an average
labor rate of $60 per work hour. Required parts will cost as much as
$874 per airplane. Based on these figures, the cost impact of the
required modification is estimated to be as much as $6,394 per
airplane.
It will take approximately 10 work hours per airplane to accomplish
the required inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the required inspection on
U.S. operators is estimated to be $42,000, or $600 per airplane, per
inspection cycle.
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.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by adding the following new
airworthiness directive:

2002-07-05 Airbus Industrie: Amendment 39-12699. Docket 99-NM-86-AD.

Applicability: All Model A300 B2, A300 B4, A300 B4-600, and A300
B4-600R series airplanes; and 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 (g) 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 propagation of cracks on the frame 40 aft
fittings due to local stress concentrations at the upper flange
runout of frame 40, which could result in reduced structural
integrity of the airplane, accomplish the following:

Modification

(a) For airplanes on which Airbus Modification 10430 has not
been done before the effective date of this AD: Concurrently with
the inspection required by paragraph (b) of this AD, modify the
profile of frame 40 aft fittings per the service information
specified in Table 1, as follows:

Table 1.--Service Information
----------------------------------------------------------------------------------------------------------------
Do the actions in
For Model-- accordance with either-- Of Airbus Service Dated--
Bulletin--
----------------------------------------------------------------------------------------------------------------
(1) A300 B2 and A300 B4 series (i) Revision 01 or..... A300-53-0296........... September 30, 1998.
airplanes.
(ii) Revision 02....... A300-53-0296........... May 12, 1999.
(2) A300 B4-600 and A300 B4-600R (i) Revision 01 or..... A300-53-6048........... September 30, 1998.
series airplanes and Model A300 F4- (ii) Revision 03....... A300-53-6048........... February 21, 2000.
605R airplanes.

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

Note 2: For Model A300 B4-600 and A300 B4-600R series airplanes
and Model A300 F4-605R airplanes: Actions performed in accordance
with Airbus Service Bulletin A300-53-6048, dated January 16, 1996;
or Revision 02, dated May 12, 1999; are

[[Page 16985]]

acceptable for compliance with the applicable requirements of this
AD.

Note 3: Airbus Service Bulletin A300-53-6048 refers to Airbus
Service Bulletin A300-53-6063 as an additional source of service
information for accomplishment of certain repairs.

Inspection

(b) For all airplanes, inspect the airplane per Table 2, as
follows:

Table 2.--Inspection Requirements
------------------------------------------------------------------------
Requirements Description
------------------------------------------------------------------------
(1) Area to inspect.................... The frame 40 AFT fitting.
(2) Type of inspection................. Nondestructive test (NDT).
(3) Compliance time.................... As specified by paragraph (c)
of this AD.
(4) Discrepancies to detect............ Cracking.
(5) Service information................ Inspect in accordance with the
applicable service bulletin
listed in Table 1 of this AD.
(6) Follow-on actions if you find no Repeat the inspection
cracking. thereafter at the applicable
interval specified by Table 3
of this AD.
(7) Corrective actions if you find Do the actions specified by
cracking. paragraph (d) of this AD.
(8) Terminating action................. The modification specified by
paragraph (e) of this AD
terminates the requirements of
this AD.
------------------------------------------------------------------------

Note 4: An NDT per Non-destructive Testing Manual 53-15-30, Part
6, Procedure C, is also acceptable for compliance with the
requirements of paragraph (b) of this AD.

(c) Perform the inspection required by paragraph (b) of this AD
per the schedule in Table 3 of this AD. For airplanes on which this
inspection has been accomplished before the effective date of this
AD, the initial compliance time may be extended by the repetitive
interval following the date the inspection was accomplished. Table 3
follows:

Table 3.--Compliance Times for Inspection
----------------------------------------------------------------------------------------------------------------
If the total flight
cycles accumulated on And repeat the
For Model-- the airplane as of the Then inspect-- inspection at least
effective date of this every--
AD is--
----------------------------------------------------------------------------------------------------------------
(1) A300 B4-600 and A300 B4-600R (i) Fewer than 6,200.. Before the airplane 7,500 flight cycles or
series airplanes and Model A300 F4- accumulates 7,700 total 17,250 flight hours,
605R airplanes, pre-Modification flight cycles or 17,710 whichever occurs
10430. total flight hours, first.
whichever occurs first.
(ii) At least 6,200 Within 1,500 flight cycles 7,500 flight cycles or
and fewer than 9,700. or 3,450 flight hours 17,250 flight hours,
after the effective date whichever occurs
of this AD, whichever first.
occurs first.
(iii) At least 9,700.. Within 750 flight cycles or 7,500 flight cycles or
1,725 flight hours after 17,250 flight hours,
the effective date of this whichever occurs
AD, whichever occurs first. first.
(2) A300 B4-600 and A300 B4-600R (i) Fewer than 19,600. Before the airplane 7,500 flight cycles or
series airplanes and Model A300 B- accumulates 21,100 total 17,250 flight hours,
4605R airplanes, post-Modification flight cycles or 48,530 whichever occurs
10430. total flight hours, first.
whichever occurs first.
(ii) At least 19,600 Within 1,500 flight cycles 7,500 flight cycles or
and fewer than 23,100. or 3,450 flight hours 17,250 flight hours,
after the effective date whichever occurs
of this AD, whichever first.
occurs first.
(iii) At least 23,100. Within 750 flight cycles or 7,500 flight cycles or
1,725 flight hours after 17,250 flight hours,
the effective date of this whichever occurs
AD, whichever occurs first. first.
(3) A300 B2 series airplanes....... (i) Fewer than 12,00.. Before the airplane 5,500 flight cycles or
accumulates 14,000 total 5,940 flight hours,
flight cycles or 15,120 whichever occurs
total flight hours, first.
whichever occurs first.
(ii) At least 12,000 Within 2,000 flight cycles 5,500 flight cycles or
and fewer than 17,000. or 2,160 flight hours 5,940 flight hours,
after the effective date whichever occurs
of this AD, whichever first.
occurs first.
(iii) At least 17,000. Within 1,000 flight cycles 5,500 flight cycles or
or 1,080 flight hours 5,940 flight hours,
after the effective date whichever occurs
of this AD, whichever first.
occurs first.
(4) A300 B4-100 series airplanes... (i) Fewer than 9,500.. Before the airplane 4,500 flight cycles or
accumulates 11,500 total 5,985 flight hours,
flight cycles or 15,295 whichever occurs
total flight hours, first.
whichever occurs first.
(ii) At least 9,500 Within 2,000 flight cycles 4,500 flight cycles or
and fewer than 14,500. or 2,660 flight hours 5,985 flight hours,
after the effective date whichever occurs
of this AD, whichever first.
occurs first.
(iii) At least 14,500. Within 1,000 flight cycles 4,500 flight cycles or
or 1,330 flight hours 5,985 flight hours,
after the effective date whichever occurs
of this AD, whichever first.
occurs first.

[[Page 16986]]

(5) A300 B4-200 series airplanes... (i) Fewer than 8,500.. Before the airplane 4,000 flight cycles or
accumulates 10,500 total 8,320 flight hours,
flight cycles or 21,840 whichever occurs
total flight hours, first.
whichever occurs first.
(ii) At least 8,500 Within 2,000 flight cycles 4,000 flight cycles or
and fewer than 13,500. or 4,160 flight hours 8,320 flight hours,
after the effective date whichever occurs
of this AD, whichever first.
occurs first.
(iii) At least 13,500. Within 1,000 flight cycles 4,000 flight cycles or
or 2,080 flight hours 8,320 flight hours,
after the effective date whichever occurs
of this AD, whichever first.
occurs first.
----------------------------------------------------------------------------------------------------------------

Note 5: An NDT inspection is also required by AD 98-25-07,
amendment 39-10933, to be repetitively performed on Model A300 B4-
600 and A300 B4-600R series airplanes and Model A300 F4-605R
airplanes on which Airbus Modification 10453 has not been installed.
For those airplanes, if the inspection is done within the applicable
compliance time specified by paragraph (c) of this AD, the threshold
for the initial inspection of paragraph (b) of this AD may be
extended by 1,500 flight cycles.

Corrective Actions

(d) If any cracking is found during any inspection required by
paragraph (b) of this AD: Except as required by paragraph (f) of
this AD, prior to further flight, perform all applicable corrective
actions in accordance with the applicable service bulletin
identified in Table 1 of this AD.

Terminating Action

(e) Accomplishment of the applicable modification in accordance
with the applicable service bulletin specified by paragraph (e)(1)
or (e)(2) of this AD terminates the requirements of this AD.
(1) For Model A300 B4-600 and A300 B4-600R series airplanes: In
accordance with Airbus Service Bulletin A300-57-6053, Revision 1,
dated October 31, 1995; or Revision 02, dated June 2, 1999.
(2) For Model A300 B2 and A300 B4 series airplanes: In
accordance with Airbus Service Bulletin A300-53-0297, Revision 2,
dated October 31, 1995.

Exception to Service Bulletin Instructions

(f) During any inspection required by this AD, if the service
bulletin specifies to contact the manufacturer for an appropriate
action: Prior to further flight, repair in accordance with a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the Direction Generale de l'Aviation
Civile (DGAC) (or its delegated agent).

Alternative Methods of Compliance

(g) 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.

Note 6: 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

(h) 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

(i) Except as required by paragraph (f) of this AD, the required
actions shall be done in accordance with the applicable service
documents identified in Table 4 and Table 5 of this AD, as follows:

Table 4.--Referenced Service Documents for Required Actions
----------------------------------------------------------------------------------------------------------------
Revision level shown on
Service bulletin and date Page numbers the page Date shown on page
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-53-0296, 1-38................... 01..................... September 30, 1998.
Revision 01, September 30, 1998.
Airbus Service Bulletin A300-53-0296, 1-3, 8, 15, 16,18, 20, 02..................... May 12, 1999.
Revision 02, May 12, 1999. 22, 23,24.
4-7, 9-14, 17, 19, 21, 01..................... September 30, 1998.
25, 26, 27-38.
Airbus Service Bulletin A300-53-6048, 1-31................... 01..................... September 30, 1998.
Revision 01, September 30, 1998.
Airbus Service Bulletin A300-53-6048, 1-32................... 03..................... February 21, 2000.
Revision 03, February 21, 2000.
----------------------------------------------------------------------------------------------------------------

Table 5.--Referenced Service Documents for Optional Terminating Action
----------------------------------------------------------------------------------------------------------------
Revision level shown on the
Service bulletin and date Page numbers page Date shown on page
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-57- 1, 7-9, 11-15, 19-24, 1.......................... October 31, 1995.
6053, Revision 1, October 31, 1995. 35, 36, 41, 42, 45-47.
2-6, 10, 16-18, 25-34, Original................... February 21, 1995.
37-40, 43, 44.

[[Page 16987]]

Airbus Service Bulletin A300-57- 1-6, 8, 23, 23a, 46, 02......................... June 2, 1999.
6053, Revision 02, June 2, 1999. 47.
7, 9, 11, 12, 13-15, 1.......................... October 31, 1995.
19-22, 35, 36, 41,
42, 45.
10, 16-18, 25, 26, 27- Original................... February 21, 1995.
34, 37-40, 43, 44.
Airbus Service Bulletin A300-53- 1-60.................. 2.......................... October 31, 1995.
0297, Revision 2, October 31, 1995.
----------------------------------------------------------------------------------------------------------------

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 7: The subject of this AD is addressed in French
airworthiness directive 1998-481-270(B) R1, dated July 12, 2000.

Effective Date

(j) This amendment becomes effective on May 14, 2002.

Issued in Renton, Washington, on March 28, 2002.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-8278 Filed 4-8-02; 8:45 am]
BILLING CODE 4910-13-P

Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R Series Airplanes; and Model A300 F4-605R Airplanes

Applicability

Unsafe Condition

Required Actions

Compliance Time

Affected Aircraft

Federal Register Abstract

Document Text

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