[Federal Register Volume 63, Number 190 (Thursday, October 1, 1998)]
[Rules and Regulations]
[Pages 52579-52583]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25953]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-109-AD; Amendment 39-10803; AD 98-20-36]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Airbus Model A300 B2 and B4 series
airplanes, that currently requires inspections for cracks of the
fuselage, wings, and vertical stabilizer structures; and repairs or
modifications, if necessary. That AD was prompted by reports of
cracking in several areas of the fuselage, wings, and vertical
stabilizer structure due to fatigue-related stress. The actions
specified by this AD are intended to prevent such fatigue-related
cracking, which could result in reduced structural integrity of the
fuselage, wing, and vertical stabilizer. This action provides for a new
optional terminating action, for certain airplanes, and expands the
applicability of the existing AD to include additional airplanes.
DATES: Effective November 5, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 5, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus, 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 86-19-02,
amendment 39-5396 (51 FR 29910, August 21, 1986), applicable to certain
Airbus Model A300 B2 and B4 series airplanes, was published in the
Federal Register on April 29, 1996 (61 FR 18700). The action proposed
to continue to require inspections for cracks of the fuselage, wings,
and vertical stabilizer structures; and repairs or modifications, if
necessary. For certain airplanes, the action also proposed to provide
for a new optional replacement action, which would constitute
terminating action for certain repetitive inspection requirements. The
actions also proposed to expand the applicability of the existing AD to
include additional airplanes.
[[Page 52580]]
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposed rule.
Changes to the Referenced Service Information
Paragraph (b)(4) of the proposed AD incorrectly lists the date of
issuance of Airbus Service Bulletin A300-53-170, Revision 1, as January
25, 1985; however, the correct date of issuance is April 26, 1982. The
final rule has been revised to correct the date of issuance for
Revision 1, and to include Revision 2 of the service bulletin, dated
February 2, 1988, as an additional source of service information.
Paragraph (e)(3) of the proposed AD incorrectly lists the date of
issuance of Airbus Service Bulletin A300-53-027, Revision 4, as January
4, 1984. However, the correct date of issuance is January 30, 1981. The
final rule has been revised accordingly.
Additionally, since the issuance of the proposed AD, the following
service bulletin revisions have been issued by the manufacturer:
Airbus Service Bulletin A300-53-100, Revision 2, dated July 11,
1995;
Airbus Service Bulletin A300-55-026, Revision 4, dated February 16,
1988; and
Airbus Service Bulletin A300-57-026, Revision 4, dated December 12,
1985.
The FAA has reviewed these later revisions and has determined that
no substantive differences exist from the service bulletin revisions
that were referenced in the proposed AD as appropriate sources of
service information. The FAA has revised paragraphs (f), (g), (h)(3),
and (h)(4) of the final rule to include these later revisions as
additional sources of service information.
The FAA also has removed NOTE 2 of the proposal from this final
rule, and has added the information specified in that note to the
applicability of this final rule. The effect of this change is that the
applicability of this AD indicates that the AD does not apply to Model
A300-600 series airplanes.
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
Approximately 7 Airbus Model A300 B2 and B4 series airplanes of
U.S. registry will be affected by this AD.
The actions that are currently required by AD 86-19-02 take
approximately 919 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. The cost of required parts will be
nominal. Based on these figures, the cost impact on U.S. operators of
the actions currently required is estimated to be $385,980, or $55,140
per airplane, per inspection cycle.
The new actions that are required in this AD will take
approximately 3 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact on U.S. operators of the new requirements of this AD is
estimated to be $1,260, or $180 per airplane.
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.
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 removing amendment 39-5396 (51 FR
29910, August 21, 1986), and by adding a new airworthiness directive
(AD), amendment 39-10803 to read as follows:
98-20-36 Airbus Industrie: Amendment 39-10803. Docket 95-NM-109-AD.
Supersedes AD 86-19-02, Amendment 39-5396.
Applicability: All Model A300 B2 and B4 series airplanes,
certificated in any category, excluding Model A300-600 series
airplanes.
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 (j) 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-related cracking, which could result in
reduced structural integrity of the fuselage, wing, and vertical
stabilizer, accomplish the following:
(a) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-127, Revision 4, dated May 10, 1984: Perform a
visual inspection to detect cracks in the upper fuselage skin at
frame 58 between stringer 5 left and stringer 5 right, in accordance
with the Accomplishment Instructions of the service bulletin, and in
accordance with the times specified in this paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (a)(1)(i) or (a)(1)(ii) of this AD.
(i) Prior to the accumulation of 18,000 total landings or 18,000
total flight hours, whichever occurs earlier; or
[[Page 52581]]
(ii) Within one year after September 26, 1986 (the effective
date of AD 86-19-02, amendment 39-5396).
(2) If no crack is detected, repeat this inspection thereafter
at intervals not to exceed 3,000 flight hours.
(3) If any crack is detected, prior to further flight, repair it
in accordance with Figure 2, ``Inspection and Repair Alternative
Chart,'' of the service bulletin.
(4) Installation of Airbus Modification 2147 (reference Airbus
Service Bulletin A300-53-110, Revision 10, dated April 7, 1986) or
Airbus Modification 2526/1693 (reference Airbus Service Bulletin
A300-53-128, Revision 5, dated May 10, 1984) constitutes terminating
action for the repetitive inspection requirements of paragraph
(a)(2) of this AD.
(b) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-101, Revision 7, dated May 10, 1984: Perform a
radiographic and ultrasonic inspection to detect cracks in the
circumferential fuselage splice plates and stringer couplings, in
accordance with the Accomplishment Instructions of the service
bulletin, and in accordance with the times specified in this
paragraph.
(1) Perform the initial inspections at the applicable time
specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD:
(i) For airplanes on which the actions specified in Airbus
Service Bulletin A300-53-053, Revision 2, dated July 30, 1981, have
been accomplished previously: Inspect prior to the accumulation of
20,000 landings since accomplishment of those actions, or within one
year after September 26, 1986, whichever occurs later.
(ii) For airplanes on which the actions specified in Airbus
Service Bulletin A300-53-053, Revision 2, dated July 30, 1981, have
not been accomplished: Inspect prior to the accumulation of 18,000
total landings, or within one year after September 26, 1986,
whichever occurs later.
(2) If no crack is detected, repeat the inspections thereafter
at intervals not to exceed 3,000 landings.
(3) If any crack is detected, prior to further flight, repair it
in accordance with Figures 1 and 2 of the service bulletin.
(4) Installation of Airbus Modification 3760 (reference Airbus
Service Bulletin A300-53-170, Revision 1, dated April 26, 1982, or
Revision 2, dated February 2, 1988) constitutes terminating action
for the repetitive inspection requirements of paragraph (b)(2) of
this AD.
(c) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-143, Revision 3, dated May 10, 1984: Perform a
visual inspection to detect cracks in frame 57A between stringers 15
and 16 (left- and right-hand), and the stringer 5 connection angle
at frame 65 (left- and right-hand), in accordance with the
Accomplishment Instructions of the service bulletin, and in
accordance with the times specified in this paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (c)(1)(i) or (c)(1)(ii) of this AD:
(i) Prior to the accumulation of 20,000 total landings; or
(ii) Within one year after September 26, 1986.
(2) If no crack is detected, repeat this inspection thereafter
at intervals not to exceed 3,000 landings.
(3) If any crack is detected, prior to further flight, repair it
in accordance with the service bulletin.
(4) Installation of Airbus Modification 2643 (reference Airbus
Service Bulletin A300-53-132, Revision 4, dated May 10, 1984)
constitutes terminating action for the repetitive inspection
requirement of paragraph (c)(2) of this AD.
(d) For airplanes having serial number 002 through 156
inclusive, on which Airbus Modification 2611 has not been installed:
Perform a visual inspection, and liquid penetrant test if
applicable, to detect cracks in the web plate and support fitting
between frames 30A and 32 at stringer 18, and between stringers 22
and 23 (left- and right-hand), in accordance with Airbus Service
Bulletin A300-53-182, Revision 3, dated March 16, 1994, and in
accordance with the times specified in this paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (d)(1)(i) or (d)(1)(ii) of this AD:
(i) Prior to the accumulation of 30,000 total landings; or
(ii) Within 1,500 landings after the effective date of this AD.
(2) If no crack is detected, repeat the inspection at the
applicable intervals specified in paragraph (d)(2)(i) or (d)(2)(ii)
of this AD.
(i) If, at the time of the most recent inspection, the airplane
has accumulated fewer than 36,000 total landings, repeat the
inspection thereafter at intervals not to exceed 3,000 landings.
(ii) If, at the time of the most recent inspection, the airplane
has accumulated 36,000 or more total landings, repeat the inspection
thereafter at intervals not to exceed 2,000 landings.
(3) If any crack is detected in the web plate between frames 30A
and 32 at stringer 18, prior to further flight, replace the web
plate and support fitting at stringer 18 (left- and right-hand) with
a new web plate and support fitting, in accordance with the service
bulletin. Accomplishment of this replacement constitutes terminating
action for the repetitive inspection requirements for stringer 18 as
required by paragraph (d)(2) of this AD.
(4) If any crack is detected in the web plate between frame 30A
and 32 between stringers 22 and 23, prior to further flight, replace
the web plate and support fitting between stringers 22 and 23 (left-
and right-hand) with a new web plate and support fitting, in
accordance with Airbus Service Bulletin A300-53-182, Revision 3,
dated March 16, 1994. Accomplishment of this replacement constitutes
terminating action for the repetitive inspection requirements for
the subject area between stringers 22 and 23 as required by
paragraph (d)(2) of this AD.
(5) Terminating action for the repetitive inspection
requirements of paragraph (d)(2) of this AD is as follows:
(i) Installation of Airbus Modification 1691 (reference Airbus
Service Bulletin A300-53-063, Revision 4, dated October 22, 1991)
between stringers 22 and 23 constitutes terminating action for the
repetitive inspection requirements of paragraph (d)(2) of this AD
for that area only.
(ii) Replacement of the web plates and support fittings at the
level of stringer 18 (left- and right-hand) with a new web plate and
support fitting, in accordance with Airbus Service Bulletin A300-53-
182, Revision 3, dated March 16, 1994, constitutes terminating
action for the repetitive inspection requirements of paragraph
(d)(2) of this AD for that stringer only.
(iii) Accomplishment of the actions specified in both paragraph
(d)(5)(i) and paragraph (d)(5)(ii) of this AD constitutes
terminating action for all repetitive inspection requirements
required by paragraph (d)(2) of this AD.
(e) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-112, Revision 2, dated July 20, 1981: Perform a
visual inspection to detect cracks of the skin from frame 28 to
frame 31 between stringers 29 and 31 (left- and right-hand), in
accordance with the Accomplishment Instructions of the service
bulletin, and in accordance with the times specified in this
paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (e)(1)(i) or (e)(1)(ii) of this AD:
(i) Prior to the accumulation of 24,000 total landings; or
(ii) Within one year after September 26, 1986.
(2) If no crack is detected, repeat the inspection at the
applicable intervals specified in paragraph (e)(2)(i) or (e)(2)(ii)
of this AD:
(i) If, at the time of the most recent inspection, the airplane
has accumulated fewer than 36,000 total landings, repeat the
inspection thereafter at intervals not to exceed 6,000 landings.
(ii) If, at the time of the most recent inspection, the airplane
has accumulated 36,000 or more total landings, repeat the inspection
thereafter at intervals not to exceed 3,000 landings.
(3) If any crack is found, prior to further flight, install
Airbus Modification 1358 in accordance with Airbus Service Bulletin
A300-53-027, Revision 4, dated January 30, 1981. Accomplishment of
this modification constitutes terminating action for the repetitive
inspection requirements of paragraph (e)(2) of this AD.
(4) Installation of Airbus Modification 1358 (reference Airbus
Service Bulletin A300-53-027, Revision 4, dated January 30, 1981)
constitutes terminating action for the repetitive inspection
requirements of paragraph (e)(2) of this AD.
(f) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-100, Revision 1, dated May 10, 1984: Perform an
internal and external visual inspection to detect cracks of the
longitudinal joint at stringer 51 (left- and right-hand) between
frames 72 and 80, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-53-100, Revision 1, dated May 10,
1984, or Revision 2, dated July 11, 1995, and in accordance with the
times specified in this paragraph.
[[Page 52582]]
(1) Perform the initial inspection at the later of the times
specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD:
(i) Prior to the accumulation of 12,000 total landings or 15,000
total flight hours, whichever occurs earlier; or
(ii) Within one year after September 26, 1986.
(2) If no crack is found, repeat the internal inspection
thereafter at intervals not to exceed 1,500 flight hours, and repeat
the external inspection thereafter at intervals not to exceed 12,000
flight hours.
(3) If any crack is detected, prior to further flight, repair it
in accordance with the service bulletin.
(4) Installation of Airbus Modification 1421 (reference Airbus
Service Bulletin A300-53-033, Revision 3, dated May 10, 1984)
constitutes terminating action for the repetitive inspection
requirements of paragraph (f)(2) of this AD.
(g) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-55-026, Revision 3, dated May 10, 1984: Perform a
visual inspection of the 6 vertical stabilizer attachment fittings
for cracks, which initiate from the rivet holes, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-55-
026, Revision 3, dated May 10, 1984, or Revision 4, dated February
16, 1988, and in accordance with the times specified in this
paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD:
(i) Prior to the accumulation of 20,000 total landings or 20,000
total flight hours, whichever occurs earlier; or
(ii) Within one year after September 26, 1986, whichever occurs
earlier.
(2) If no crack is detected, repeat the inspection thereafter at
intervals not to exceed 1,500 landings.
(3) If any crack is detected, prior to further flight, repair it
in accordance with the service bulletin.
(4) Installation of Airbus Modification 3172 (reference Airbus
Service Bulletin A300-55-024, Revision 4, dated May 25, 1984)
constitutes terminating action for the repetitive inspection
requirements of paragraph (g)(2) of this AD.
(h) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-57-109, Revision 1, dated July 10, 1982: Perform a
visual inspection to detect cracks in the landing angle attached to
the outboard side of the wing leading edge at nose rib 8 (left- and
right-hand), in accordance with the Accomplishment Instructions of
the service bulletin, and in accordance with the times specified in
this paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (h)(1)(i) or (h)(1)(ii):
(i) Prior to the accumulation of 15,000 total landings; or
(ii) Within one year after September 26, 1986.
(2) If no crack is detected, repeat the inspection thereafter at
intervals not to exceed 3,000 landings.
(3) If any crack is detected, within the next 1,000 landings
following crack detection, install Airbus Modification 1307 in
accordance with Airbus Service Bulletin A300-57-026, Revision 3,
dated October 21, 1982, or Revision 4, dated December 12, 1985.
(4) Installation of Airbus Modification 1307 (reference Airbus
Service Bulletin A300-57-026, Revision 3, dated October 21, 1982, or
Revision 4, dated December 12, 1985) constitutes terminating action
for the repetitive inspection requirements of paragraph (h)(2) of
this AD.
(i) 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.
(j) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager, International
Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(k) The actions shall be done in accordance with the following
Airbus service bulletins, as applicable, which contain the specified
list of effective pages:
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Service bulletin referenced and
date Page No. Revision level shown on page Date shown on page
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A300-53-127, Revision 4, May 10, 1-5, 11, 12............................. 4...................................... May 10, 1984.
1984.
6-10, 13................................ Original............................... April 17, 1980.
A300-53-101, Revision 7, May 10, 1, 2.................................... 7...................................... May 10, 1984.
1984.
3, 7.................................... 5...................................... September 10, 1982.
4-6, 8, 9............................... 4...................................... June 15, 1981.
A300-53-143, Revision 3, May 10, 1, 2, 5, 8.............................. 3...................................... May 10, 1984.
1984.
3, 4, 6, 7, 9........................... Original............................... September 28, 1981.
A300-53-182, Revision 3, March 16, 1-20.................................... 3...................................... March 16, 1994.
1994.
A300-53-112, Revision 2, July 20, 1....................................... 2...................................... July 20, 1981.
1981.
2, 3.................................... Original............................... December 28, 1979.
A300-53-027, Revision 4, January 1, 15................................... 4...................................... January 30, 1981.
30, 1981.
2....................................... 3...................................... October 23, 1979.
3-14.................................... Original............................... March 14, 1976.
A300-53-100, Revision 1, May 10, 1-4..................................... 1...................................... May 10, 1984.
1984.
5-9..................................... Original............................... September 14, 1979.
A300-53-100, Revision 2, July 11, 1, 4.................................... 2...................................... July 11, 1995.
1995.
2, 3.................................... 1...................................... May 10, 1984.
5-9..................................... Original............................... September 14, 1979.
A300-55-026, Revision 3, May 10, 1, 7.................................... 3...................................... May 10, 1984.
1984.
2-6, 8, 9............................... 2...................................... October 10, 1981.
A300-55-026, Revision 4, February 1-5..................................... 4...................................... February 16, 1988.
16, 1988.
6, 8, 9................................. 2...................................... October 10, 1981.
7....................................... 3...................................... May 10, 1984.
A300-57-109, Revision 1, July 10, 1-4..................................... 1...................................... July 10, 1982.
1982.
A300-57-026, Revision 3, October 1, 2.................................... 3...................................... October 21, 1982.
21, 1982.
3, 5-17................................. Original............................... August 2, 1976.
4....................................... 1...................................... December 2, 1976.
A300-57-026, Revision 4, December 1....................................... 4...................................... December 12, 1985.
12, 1985.
2....................................... 3...................................... October 21, 1982.
3, 5-17................................. Original............................... August 2, 1976.
4....................................... 1...................................... December 2, 1976.
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[[Page 52583]]
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 3: The subject of this AD is addressed in French
airworthiness directive 83-102-053(B)R2, dated March 2, 1994.
(l) This amendment becomes effective on November 5, 1998.
Issued in Renton, Washington, on September 22, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-25953 Filed 9-30-98; 8:45 am]
BILLING CODE 4910-13-P
