[Federal Register Volume 65, Number 103 (Friday, May 26, 2000)]
[Rules and Regulations]
[Pages 34069-34072]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-12816]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-99-AD; Amendment 39-11739; AD 2000-10-15]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes two existing airworthiness
directives (AD), applicable to certain Airbus Model A320 series
airplanes, that currently require modification of the rear spar web of
the wing and cold expansion of certain attachment holes for the forward
pintle fitting and certain holes at the actuating cylinder anchorage of
the main landing gear (MLG). This amendment adds a requirement for
repetitive inspections to detect fatigue cracking in certain areas of
the rear spar of the wing, and corrective action, if necessary. This
[[Page 34070]]
amendment also provides for optional terminating action for the
requirements of this AD. 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 detect and correct fatigue cracking, which may lead to reduced
structural integrity of the wing and the MLG.
DATES: Effective June 30, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 30, 2000.
The incorporation by reference of certain other publications was
approved previously by the Director of the Federal Register as of June
11, 1993 (58 FR 27923, May 12, 1993), and February 14, 1994 (59 FR
1903, January 13, 1994).
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 93-08-15,
amendment 39-8563 (58 FR 27923, May 12, 1993), and AD 93-25-13,
amendment 39-8777 (59 FR 1903, January 13, 1994), which are both
applicable to certain Airbus Model A320 series airplanes, was published
in the Federal Register on February 10, 2000 (65 FR 6566). The action
proposed to continue to require modification of the wing rear spar web
and cold expansion of certain attachment holes for the forward pintle
fitting and certain holes at the actuating cylinder anchorage of the
MLG. The AD proposed to add a requirement for repetitive ultrasonic
inspections to detect fatigue cracking in certain areas of the wing
rear spar, and repair of cracking. The AD also proposed to provide for
optional terminating action for the inspections proposed by this AD.
Comments Received
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Proposal
One commenter concurs with the proposed AD. Another commenter
states that Airbus Production Modification 24591 is installed on its
airplanes; therefore, it is not affected by the proposed AD.
Inspection Threshold for Certain Airplanes
One commenter requests that the proposed AD be revised to allow
``Group 2'' airplanes to accomplish the initial inspection of the wing
rear spar within 12,000 flight cycles after accomplishment of Airbus
Service Bulletin A320-57-1060. The commenter defines ``Group 1''
airplanes as manufacturer's serial numbers (MSN) 002 through 021, on
which Airbus Service Bulletins A320-57-1004 and A320-57-1060 are
accomplished as retrofit. ``Group 2'' airplanes are defined as MSN's
022 through 051, on which Airbus Modification 20740 (equivalent to
A320-57-1004) has been accomplished in production, and Airbus Service
Bulletin A320-57-1060 as retrofit.
The commenter notes that ``Group 1'' airplanes are granted 12,000
flight cycles after accomplishment of A320-57-1060, yet ``Group 2''
airplanes are required to undergo inspection prior to accumulation of
17,300 total flight cycles, regardless of when modification per A320-
57-1060 was accomplished. The commenter states that ``Group 1'' and
``Group 2'' airplanes are in the same configuration and will have a
similar fatigue life; therefore, both should have the same inspection
threshold.
The FAA does not concur. Although the FAA acknowledges that ``Group
1'' and ``Group 2'' airplanes may be in a similar modification
configuration, the design configuration of these airplanes is
different. ``Group 1'' airplanes are composed of Model A320-100 series
airplanes, and ``Group 2'' airplanes are composed of Model A320-200
series airplanes. Model A320-200 series airplanes are equipped with a
center fuel tank (not installed on Model A320-100 series airplanes)
that increases the airplanes' weight. For this reason, it is necessary
that ``Group 2'' airplanes be inspected for cracking prior to
accumulation of 17,300 total flight cycles, regardless of when Service
Bulletin A320-57-1060 is accomplished. No change is made to the final
rule.
Terminating Modification for Certain Airplanes
One commenter requests that modification in accordance with Airbus
Service Bulletin A320-57-1089 be considered as terminating action to
all inspection requirements if accomplished prior to the initial
inspection interval, or to repetitive inspections if accomplished after
the initial inspection interval. The commenter states that terminating
action credit is allowed under paragraph (e) of the proposed AD only if
accomplished prior to 12,000 total flight cycles. The commenter states
that accomplishment of the terminating modification includes a non-
destructive test inspection of the inner rear spar at each hole
location. Since this inspection during the modification will ensure
that the inner rear spar is free of defects, terminating action to the
follow-on inspection requirements should also be provided.
The FAA notes that terminating modification to the inspection
requirements of the AD is already provided for in paragraph (e) of the
proposed AD, and considers that clarification of the provisions for
terminating modification is necessary. As stated in the second sentence
of paragraph (e) of the AD, the threshold of 12,000 total flight cycles
is required only if modification per Service Bulletin A320-57-1089 is
chosen in lieu of accomplishing the modifications required by
paragraphs (a) and (b) of the AD. However, the modification also
constitutes acceptable terminating action for the ultrasonic inspection
requirements of the AD, as stated in the first sentence of paragraph
(e) of the AD. Paragraph (e) has been revised to more clearly specify
the terminating action provisions of the AD.
Cost Estimate for Terminating Modification
Two commenters request that the proposed AD be revised to provide
correct cost estimates for the optional modification described in
Airbus Service Bulletin A320-57-1089. The commenters state that the
service bulletin lists the labor cost as 980 work hours, yet the
proposed AD provides an estimate of 750 work hours.
The FAA acknowledges that the service bulletin estimate specifies
additional work hours (for access and close) that are not included in
the proposed AD. However, the cost impact information in an AD
typically describes only the ``direct'' costs of
[[Page 34071]]
specific actions, and does not include incidental costs, such as the
time required to gain access and close up; planning time; or time
necessitated by other administrative actions. Because incidental costs
may vary significantly from operator to operator, they are almost
impossible to calculate. Additionally, since this is an optional
modification, operators may choose not to incur such costs, or may
minimize costs by accomplishing the modification during scheduled
maintenance. No change is made to the final rule.
Additional Changes to the AD
To clarify actions for airplanes on which modifications have been
installed in production and those on which service bulletins have been
accomplished as retrofit, the FAA has revised paragraph (c)(2) of the
AD to refer to certain modifications as ``Airbus Production
Modification * * *.'' Additionally, a heading has been included to
specify the actions required by paragraphs (c) and (d) of the AD.
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 changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 126 airplanes of U.S. registry that will be
affected by this AD.
It takes approximately 60 work hours per airplane to accomplish the
modification of the rear spar web of the wing, as required by AD 93-08-
15 and retained in this AD, at an average labor rate of $60 per work
hour. Based on these figures, the total cost impact of the modification
on U.S. operators is estimated to be $3,600 per airplane.
It takes approximately 600 work hours per airplane to accomplish
the cold expansion of certain holes associated with the MLG, as
required by AD 93-25-13 and retained in this AD, at an average labor
rate of $60 per work hour. Required parts are provided by the
manufacturer at no cost to the operators. Based on these figures, the
total cost impact of the cold expansion on U.S. operators is estimated
to be $36,000 per airplane.
The new inspection that is required by this new AD will take
approximately 24 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the new requirements of this AD on U.S. operators is
estimated to be $181,440, or $1,440 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.
Should an operator elect to accomplish the optional terminating
action specified in this AD, it would take approximately 750 work
hours, at an average labor rate of $60 per work hour. The required
parts would cost $27,036; $30,595; or $32,727; depending on the
airplane configuration. Based on these figures, the cost per airplane
of the optional terminating action provided by this AD is estimated to
be $72,036; $75,595; or $77,727.
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 removing amendments 39-8563 (58 FR
27923, May 12, 1993) and 39-8777 (59 FR 1903, January 13, 1994), and by
adding a new airworthiness directive (AD), amendment 39-11739, to read
as follows:
2000-10-15 Airbus Industrie: Amendment 39-11739. Docket 98-NM-99-
AD. Supersedes AD 93-08-15, Amendment 39-8563; and AD 93-25-13,
Amendment 39-8777.
Applicability: Model A320 series airplanes, certificated in any
category, except those on which Airbus Modification 24591 (Airbus
Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01,
dated April 17, 1997; or Revision 02, dated November 6, 1998) has
been accomplished.
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 (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 detect and correct fatigue cracking in certain areas of the
rear spar of the wing, which may lead to reduced structural
integrity of the wing and the main landing gear (MLG), accomplish
the following:
Restatement of Actions Required by AD 93-08-15
(a) For airplanes having manufacturer's serial numbers (MSN) 003
through 008 inclusive, and 010 through 021 inclusive: Prior to the
accumulation of 12,000 total flight cycles, or within 500 flight
cycles after June 11, 1993 (the effective date of AD 93-08-15,
amendment 39-8563), whichever occurs later, modify the inner rear
spar web of the wing in accordance with Airbus Service Bulletin
A320-57-1004, Revision 1, dated September 24, 1992, or Revision 2,
dated June 14, 1993.
Restatement of Actions Required by AD 93-25-13
(b) For airplanes having MSN's 002 through 051 inclusive: Prior
to the accumulation of 12,000 total flight cycles, or within 2,000
flight cycles after February 14, 1994 (the effective date of AD 93-
25-13,
[[Page 34072]]
amendment 39-8777), whichever occurs later, accomplish the
requirements of paragraphs (b)(1) and (b)(2) of this AD in
accordance with Airbus Service Bulletin A320-57-1060, dated December
8, 1992; or Revision 2, dated December 16, 1994.
(1) Perform a cold expansion of all the attachment holes for the
forward pintle fitting of the MLG, except for the holes that are for
taper-lok bolts.
(2) Perform a cold expansion of the holes at the actuating
cylinder anchorage of the MLG.
Note 2: Accomplishment of the cold expansion in accordance with
Airbus Service Bulletin A320-57-1060, Revision 1, dated April 26,
1993, is also acceptable for compliance with the requirements of
paragraph (b) of this AD.
New Actions Required by This AD
Ultrasonic Inspections and Corrective Action
(c) For all airplanes: Perform an ultrasonic inspection to
detect cracking of the rear spar of the wing, in accordance with
Airbus Service Bulletin A320-57-1088, Revision 02, dated July 29,
1999; at the applicable time specified by paragraph (c)(1) or (c)(2)
of this AD. Repeat the inspection thereafter at intervals not to
exceed 3,600 flight cycles.
(1) For airplanes on which the actions specified by Airbus
Service Bulletin A320-57-1004, Revision 2, dated June 14, 1993, or
earlier version; and Airbus Service Bulletin A320-57-1060, Revision
02, dated December 16, 1994, or earlier version; have been
accomplished: Perform the inspection of all applicable fastener
holes within 12,000 flight cycles after accomplishment of the
service bulletins, or within 750 flight cycles after the effective
date of this AD, whichever occurs later.
(2) For airplanes on which the actions specified by Airbus
Production Modification 20740 and Airbus Service Bulletin A320-57-
1060, Revision 2, dated December 16, 1994, or earlier version, have
been accomplished; or on which Airbus Production Modifications
20740, 20741, and 20796 have been accomplished: Perform the
inspections at the locations and applicable times specified by
paragraphs (c)(2)(i) and (c)(2)(ii) of this AD.
(i) Perform the inspection of left and right fastener holes 52
to 55, 82, 83, 87, and 88; located in the rear spar of the wing;
prior to the accumulation of 17,300 total flight cycles, or within
750 flight cycles after the effective date of this AD, whichever
occurs later. If any cracking is found, prior to further flight,
accomplish the requirements of paragraph (c)(2)(ii) of this AD.
(ii) Except as required by paragraph (c)(2)(i) of this AD:
Perform the inspection of all fastener holes located in the rear
spar of the wing that are not identified in paragraph (c)(2)(i) of
this AD prior to the accumulation of 20,000 total flight cycles, or
within 200 flight cycles after the effective date of this AD,
whichever occurs later.
Note 3: Accomplishment of the actions specified by Airbus
Service Bulletin A320-57-1088, dated September 30, 1996, or Revision
01, dated September 17, 1997, prior to the effective date of this AD
is acceptable for compliance with the requirements of the initial
inspection required by paragraph (c) of this AD.
(d) If any crack is found during any inspection required by
paragraph (c) of this AD: 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). For a repair method to be approved by the Manager,
International Branch, ANM-116, as required by this paragraph, the
Manager's approval letter must specifically reference this AD.
Optional Terminating Action
(e) Modification of all specified fastener holes in the rear
spar of the wing in accordance with Airbus Service Bulletin A320-57-
1089, dated December 22, 1996; Revision 01, dated April 17, 1997; or
Revision 02, dated November 6, 1998; constitutes terminating action
for the ultrasonic inspections required by paragraph (c) of this AD.
Such modification, if accomplished prior to the accumulation of
12,000 total flight cycles, also constitutes terminating action for
the actions required by paragraphs (a) and (b) of this AD.
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 93-25-13; amendment 39-8777, are approved as
alternative methods of compliance with this AD.
Note 4: 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
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.
Incorporation by Reference
(h) Except as required by paragraph (d) of the AD, the actions
shall be done in accordance with Airbus Service Bulletin A320-57-
1004, Revision 1, dated September 24, 1992; Airbus Service Bulletin
A320-57-1004, Revision 2, dated June 14, 1993; Airbus Service
Bulletin A320-57-1060, dated December 8, 1992; Airbus Service
Bulletin A320-57-1060, Revision 2, dated December 16, 1994; or
Airbus Service Bulletin A320-57-1088, Revision 02, including
Appendix 01, dated July 29, 1999; as applicable. Airbus Service
Bulletin A320-57-1004, Revision 2, dated June 14, 1993, contains the
following list of effective pages:
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Revision level shown on
Page No. page Date shown on page
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1, 4, 12, 14, 17-20, 22, 23, 28, 29...... 2.......................... June 14, 1993.
15....................................... 1.......................... September 24, 1992.
2, 3, 5-11, 13, 16, 21, 24-27, 30........ Original................... July 9, 1991.
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(1) The incorporation by reference of Airbus Service Bulletin
A320-57-1004, Revision 2, dated June 14, 1993; Airbus Service
Bulletin A320-57-1060, Revision 2, dated December 16, 1994; and
Airbus Service Bulletin A320-57-1088, Revision 02, including
Appendix 01, dated July 29, 1999; is approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51.
(2) The incorporation by reference of Airbus Service Bulletin
A320-57-1004, Revision 1, dated September 24, 1992, was approved
previously by the Director of the Federal Register as of June
11,1993 (58 FR 27923, May 12, 1993).
(3) The incorporation by reference of Airbus Service Bulletin
A320-57-1060, dated December 8, 1992, was approved previously by the
Director of the Federal Register as of February 14, 1994 (59 FR
1903, January 13, 1994).
(4) 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 5: The subject of this AD is addressed in French
airworthiness directive 1999-264-135(B), dated June 30, 1999.
(i) This amendment becomes effective on June 30, 2000.
Issued in Renton, Washington, on May 16, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-12816 Filed 5-25-00; 8:45 am]
BILLING CODE 4910-13-U