[Federal Register Volume 61, Number 102 (Friday, May 24, 1996)]
[Rules and Regulations]
[Pages 26091-26094]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-12731]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-85-AD; Amendment 39-9630; AD 96-11-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Industrie Model A300, A300-600,
and A310 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Industrie Model A300, A300-600, and A310
series airplanes, that requires inspections to detect cracks in the
lower spar axis of the pylons between ribs 6 and 7, and repair, if
necessary. This amendment is prompted by reports that fatigue cracking
has been found on the lower spar of the pylon. The actions specified by
this AD are intended to prevent such fatigue cracking, which could
result in reduced structural integrity of the lower spar of the pylon.
DATES: Effective June 28, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 28, 1996.
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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 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 certain Airbus Industrie Model
A300, A300-600, and A310 series airplanes was published in the Federal
Register on March 6, 1996 (61 FR 8892). That action proposed to require
inspections to detect cracks in the lower spar axis of the pylons
between ribs 6 and 7, and repair, if necessary.
Interested persons have been afforded an opportunity to participate
in the
[[Page 26092]]
making of this amendment. Due consideration has been given to the
comments received.
Support for the Proposal
One commenter supports the proposed rule.
Request To Revise Compliance Threshold for Inspection
One commenter requests that the inspection threshold specified in
paragraph (h) of the proposal be revised from 14,500 landings to 17,000
landings for consistency with the threshold provided in Airbus Service
Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
The FAA concurs with the commenter's request. The FAA's intent is
that the inspection threshold and repetitive inspection interval
specified in paragraph (h) of this AD parallel the threshold and
interval recommended in the Airbus service bulletin. The FAA has
revised paragraph (h) of the final rule to specify an inspection
threshold of 17,000 landings. The repetitive inspection interval of
14,500 landings, which was recommended in the Airbus service bulletin,
remains unchanged in this final rule.
Correction of Service Bulletin Number
The FAA has revised the reference to a service bulletin number that
appeared in paragraph (i) of the proposed AD as Airbus Industrie
Service Bulletin A300-54-2017. The correct service bulletin number is
A310-54-2017.
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
The FAA estimates that 99 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 8 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $60 per work hour. Based on these figures, the cost impact of
the AD on U.S. operators is estimated to be $47,520, or $480 per
airplane, per inspection cycle.
The cost impact figure discussed above is 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 of a Model A300 series airplane elect to
accomplish the optional modification that is provided by this AD
action, it will take approximately 100 work hours to accomplish, at an
average labor rate of $60 per work hour. The cost of required parts
will be approximately $1,500 per airplane. Based on these figures, the
cost impact of the optional modification for Model A300 series
airplanes is estimated to be $7,500 per airplane.
Should an operator of a Model A300-600 or A310 series airplane
elect to accomplish the optional modification that is provided by this
AD action, it will take approximately 110 work hours to accomplish, at
an average labor rate of $60 per work hour. The cost of required parts
will be approximately $1,500 per airplane. Based on these figures, the
cost impact of the optional modification for Model A300-600 and A310
series airplanes is estimated to be $8,100 per airplane.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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:
96-11-05 Airbus Industrie: Amendment 39-9630. Docket 95-NM-85-AD.
Applicability: Model A300, A300-600, and A310 series airplanes;
as listed in Airbus Industrie Service Bulletins A300-54-0073, A300-
54-6014, and A310-54-2017, all Revision 1, all dated March 28, 1994;
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 (k) 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 reduced structural integrity of the lower spar,
accomplish the following:
(a) For Model A300 series airplanes equipped with General
Electric CF6-50C engines, and having pylons that have not been
modified in accordance with Airbus Industrie Service Bulletin A300-
54-0080, Revision 1, dated January 16, 1995: Prior to the
accumulation of 10,900 total landings, or within 500 landings after
the effective date of this AD, whichever occurs later, perform an
internal eddy current inspection to detect cracks in the lower spar
axis of the pylons between ribs 6 and 7, in accordance with Airbus
Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28,
1994.
(1) If no crack is found, repeat the inspection thereafter at
intervals not to exceed 6,700 landings.
(2) If any crack is found that is less than 35 mm, prior to
further flight, stop-drill the crack in accordance with the
procedures specified in Section 51-41-10 of the Structural Repair
Manual (SRM). Thereafter, prior to the accumulation of 250 landings
after crack discovery, repair in accordance with the service
bulletin. Prior to the accumulation of 17,900 landings after
accomplishing the repair, perform an eddy current inspection to
detect cracks at the stiffener ends, ribs 6 and 7, at the edge of
the holes made during the repair and on the fasteners located at the
edge of the doubler, in accordance with the service bulletin.
[[Page 26093]]
(i) If no crack is found, repeat the inspection required by
paragraph (a)(2) of this AD thereafter at intervals not to exceed
15,000 landings.
(ii) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113, FAA, Transport Airplane Directorate.
(3) If any crack is found that is greater than or equal to 35
mm, prior to further flight, repair in accordance with a method
approved by the Manager, Standardization Branch, ANM-113.
(b) For Model A300 series airplanes equipped with General
Electric CF6-50C engines, and having pylons that have been modified
in accordance with Airbus Industrie Service Bulletin A300-54-0080,
Revision 1, dated January 16, 1995: Prior to the accumulation of
30,300 landings since installation of the modification, or within
500 landings after the effective date of this AD, whichever occurs
later, perform an eddy current inspection to detect cracks in the
lower spar axis of the pylons between ribs 6 and 7, in accordance
with Airbus Industrie Service Bulletin A300-54-0073, Revision 1,
dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection
thereafter at intervals not to exceed 21,300 landings.
(2) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(c) For Model A300 series airplanes equipped with Pratt &
Whitney JT9D-59A engines, and having pylons that have not been
modified in accordance with Airbus Industrie Service Bulletin A300-
54-0080, Revision 1, dated January 16, 1995: Prior to the
accumulation of 8,600 total landings, or within 500 landings after
the effective date of this AD, whichever occurs later, perform an
internal eddy current inspection to detect cracks in the lower spar
axis of the pylons between ribs 6 and 7, in accordance with Airbus
Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28,
1994.
(1) If no crack is found, repeat the inspection thereafter at
intervals not to exceed 5,700 landings.
(2) If any crack is found that is less than 35 mm, prior to
further flight, stop-drill the crack in accordance with the
procedures specified in Section 51-41-10 of the SRM. Thereafter,
prior to the accumulation of 250 landings after crack discovery,
repair in accordance with the service bulletin. Prior to the
accumulation of 14,200 landings after accomplishing the repair,
perform an eddy current inspection to detect cracks at the stiffener
ends, ribs 6 and 7, at the edge of the holes made during the repair
and on the fasteners located at the edge of the doubler, in
accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by
paragraph (c)(2) of this AD thereafter at intervals not to exceed
12,800 landings.
(ii) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35
mm, prior to further flight, repair in accordance with a method
approved by the Manager, Standardization Branch, ANM-113. -
(d) For Model A300 series airplanes equipped with Pratt &
Whitney JT9D-59A engines, and having pylons that have been modified
in accordance with Airbus Industrie Service Bulletin A300-54-0080,
Revision 1, dated January 16, 1995: Prior to the accumulation of
24,000 landings since installation of the modification, or within
500 landings after the effective date of this AD, whichever occurs
later, perform an eddy current inspection to detect cracks in the
lower spar axis of the pylons between ribs 6 and 7, in accordance
with Airbus Industrie Service Bulletin A300-54-0073, Revision 1,
dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection
thereafter at intervals not to exceed 18,200 landings.
(2) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(e) For Model A300-600 series airplanes equipped with General
Electric CF6-80C2 engines, and having pylons that have not been
modified in accordance with Airbus Industrie Service Bulletin A300-
54-6020, dated February 22, 1994: Prior to the accumulation of 9,400
total landings, or within 500 landings after the effective date of
this AD, whichever occurs later, perform an internal eddy current
inspection to detect cracks in the lower spar axis of the pylons
between ribs 6 and 7, in accordance with Airbus Industrie Service
Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at
intervals not to exceed 6,100 landings.
(2) If any crack is found that is less than or equal to 35 mm,
prior to further flight, stop-drill the crack in accordance with the
procedures specified in Section 51-41-10 of the SRM. Thereafter,
prior to the accumulation of 250 landings after crack discovery,
repair in accordance with the service bulletin. Prior to the
accumulation of 15,600 landings after accomplishing the repair,
perform an eddy current inspection to detect cracks at the stiffener
ends, ribs 6 and 7, at the edge of the holes made during the repair
and on the fasteners located at the edge of the doubler, in
accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by
paragraph (e)(2) of this AD thereafter at intervals not to exceed
13,600 landings.
(ii) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35
mm, prior to further flight, repair in accordance with a method
approved by the Manager, Standardization Branch, ANM-113.
(f) For Model A300-600 series airplanes equipped with General
Electric CF6-80C2 engines, and having pylons that have been modified
in accordance with Airbus Industrie Service Bulletin A300-54-6020,
dated February 22, 1994: Prior to the accumulation of 26,400
landings since installation of the modification, or within 500
landings after the effective date of this AD, whichever occurs
later, perform an eddy current inspection to detect cracks in the
lower spar axis of the pylons between ribs 6 and 7, in accordance
with Airbus Industrie Service Bulletin A300-54-6014, Revision 1,
dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection
thereafter at intervals not to exceed 19,400 landings.
(2) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(g) For Model A300-600 series airplanes equipped with Pratt &
Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have not
been modified in accordance with Airbus Industrie Service Bulletin
A300-54-6020, dated February 22, 1994: Prior to the accumulation of
5,700 total landings, or within 500 landings after the effective
date of this AD, whichever occurs later, perform an internal eddy
current inspection to detect cracks in the lower spar axis of the
pylons between ribs 6 and 7, in accordance with Airbus Industrie
Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at
intervals not to exceed 4,400 landings.
(2) If any crack is found that is less than 35 mm, prior to
further flight, stop-drill the crack in accordance with the
procedures specified in Section 51-41-10 of the SRM. Thereafter,
prior to the accumulation of 250 landings after crack discovery,
repair in accordance with the service bulletin. Prior to the
accumulation of 10,100 landings after accomplishing the repair,
perform an eddy current inspection to detect cracks at the stiffener
ends, ribs 6 and 7, at the edge of the holes made during the repair
and on the fasteners located at the edge of the doubler, in
accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by
paragraph (g)(2) of this AD thereafter at intervals not to exceed
10,000 landings.
(ii) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35
mm, prior to further flight, repair in accordance with a method
approved by the Manager, Standardization Branch, ANM-113.
(h) For Model A300-600 series airplanes equipped with Pratt &
Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have
been modified in accordance with Airbus Industrie Service Bulletin
A300-54-6020, dated February 22, 1994: Prior to the accumulation of
17,000 landings since installation of the modification, or within
500 landings after the effective date of this AD, whichever occurs
later, perform an eddy current inspection to detect cracks in the
lower spar axis of the pylons between ribs 6 and 7, in accordance
with Airbus Industrie Service Bulletin A300-54-6014, Revision 1,
dated March 28, 1994.
[[Page 26094]]
(1) If no crack is found, repeat the eddy current inspection
thereafter at intervals not to exceed 14,500 landings.
(2) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(i) For Model A310 series airplanes equipped with General
Electric CF6-80C2, or Pratt & Whitney JT9D-7R4, or Pratt & Whitney
PW4000 engines: Prior to the accumulation of 36,700 total landings,
or within 500 landings after the effective date of this AD,
whichever occurs later, perform an internal eddy current inspection
to detect cracks in the lower spar axis of the pylons between ribs 6
and 7, in accordance with Airbus Industrie Service Bulletin A310-54-
2017, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at
intervals not to exceed 15,000 landings.
(2) If any crack is found that is less than 35 mm, prior to
further flight, stop-drill the crack in accordance with the
procedures specified in Section 51-41-10 of the SRM. Thereafter,
prior to the accumulation of 250 landings after crack discovery,
repair in accordance with the service bulletin. Prior to the
accumulation of 40,000 landings after accomplishing the repair,
perform an eddy current inspection to detect cracks at the stiffener
ends, ribs 6 and 7, at the edge of the holes made during the repair
and on the fasteners located at the edge of the doubler, in
accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by
paragraph (i)(2) of this AD thereafter at intervals not to exceed
33,000 landings.
(ii) If any crack is found, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35
mm, prior to further flight, repair in accordance with a method
approved by the Manager, Standardization Branch, ANM-113.
(j) For Model A310 series airplanes equipped with General
Electric CF6-80C2, or Pratt & Whitney JT9D-7R4, or Pratt & Whitney
PW4000 engines: Accomplishment of the modification specified in
Airbus Industrie Service Bulletin A310-54-2023, dated October 15,
1993, constitutes terminating action for the inspections required by
paragraph (i) of this AD.
(k) 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, Standardization Branch, ANM-113.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(l) 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.
(m) The actions shall be done in accordance with the following
Airbus Industrie service bulletins, which contain the specified
effective pages:
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Service bulletin referenced and Revision level shown on
date Page No.- page Date shown on page
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A300-54-0073, Revision 1, March 1,5.......................... 1...................... Mar. 28, 1994.
28, 1994.
2-4, 6-36.................... Original............... Oct. 15, 1993.
A300-54-6014, Revision 1, March 1-4, 13...................... 1...................... Mar. 28, 1994.
28, 1994.
5-12, 14-44.................. Original............... Oct. 15, 1993.
A310-54-2017, Revision 1, March 1, 5,........................ 1...................... Mar. 28, 1994.
28, 1994.
2-4, 6-48.................... Original............... Oct. 15, 1993.
A310-54-2023, October 15, 1993. 1-38......................... Original............... Oct. 15, 1993.
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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.
(n) This amendment becomes effective on June 28, 1996.
Issued in Renton, Washington, on May 15, 1996.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-12731 Filed 5-23-96; 8:45 am]
BILLING CODE 4910-13-U
