[Federal Register Volume 61, Number 166 (Monday, August 26, 1996)]
[Rules and Regulations]
[Pages 43650-43652]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-21458]


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


DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-263-AD; Amendment 39-9724; AD 96-17-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes, Excluding Model A300-600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A300 B2 and B4 series 
airplanes, that currently requires repetitive visual inspections to 
detect cracks in the forward intermediate section skin at frame 30A 
where it joins stringer 30, and repair, if necessary. This amendment 
adds a requirement for eddy current inspection(s) to detect cracks of 
the outer skin of the fuselage; accomplishment of this inspection 
terminates the repetitive visual inspections. This amendment also 
requires repair of any cracked area and modification of the structure 
at certain frames. This amendment is prompted by in-service experience 
which has identified fatigue cracks in this area. The actions specified 
by this AD are intended to prevent fatigue cracking, which could result 
in rapid decompression of the airplane.

DATES: Effective September 30, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 30, 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) by superseding AD 90-11-09,

[[Page 43651]]

amendment 39-6611 (55 FR 21185, May 23, 1990), which is applicable to 
certain Airbus Model A300 B2 and B4 series airplanes, was published in 
the Federal Register on April 30, 1996 (61 FR 18995). That action 
proposed to continue to require repetitive detailed visual inspections 
to detect cracks of the forward intermediate section skin of the 
fuselage at the junction of frame 30A and stringer 30. However, that 
action also proposed to add a requirement to accomplish eddy current 
inspections to detect cracks of the outer skin of the fuselage at 
frames 28A and 30A above stringer 30. Accomplishment of this inspection 
action would constitute terminating action for the currently-required 
repetitive detailed visual inspections. The action also proposed to 
require the repair of any cracked area, and modification of the 
structure at frames 28A and 30A between stringer 27 and 30 (left- and 
right-hand).
    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.

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.

Cost Impact

    There are approximately 24 Airbus Model A300 B2 and B4 series 
airplanes, excluding Model A300-600 series airplanes, of U.S. registry 
that will be affected by this proposed AD.
    The detailed visual inspections that are currently required by AD 
90-11-09 take approximately 1 work hour 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 currently required detailed visual 
inspections is estimated to be $1,440, or $60 per airplane, per 
inspection cycle.
    The eddy current inspection that is required by this new AD action 
will take approximately 1 work hour 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 eddy current inspection 
requirements of this AD is estimated to be $1,440, or $60 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.

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 39-6611 (55 FR 
21185, May 23, 1990), and by adding a new airworthiness directive (AD), 
amendment 39-9724, to read as follows:

96-17-14 Airbus Industrie: Amendment 39-9724. Docket 95-NM-263-AD. 
Supersedes AD 90-11-09, Amendment 39-6611.

    Applicability: Model A300 B2 and B4 series airplanes, 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (f) 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.
    Note 2: Airbus Model A300-600 series airplanes are not subject 
to this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue cracking, which could result in rapid 
decompression of the airplane, accomplish the following:
    (a) For airplanes on which Airbus All Operators Telex (AOT) 53/
90/01, dated April 12, 1990 has been accomplished: Prior to the 
accumulation of 18,000 total landings or 24,000 total hours time-in-
service, whichever occurs first, or within 100 landings after June 
11, 1990 (the effective date of AD 90-11-09, amendment 39-6611), 
whichever occurs later, perform a detailed visual inspection to 
detect cracks of the forward intermediate section skin of the 
fuselage at the junction of frame 30A and stringer 30, in accordance 
with Airbus All Operators Telex 53/90/01, dated April 12, 1990.
    (1) If no cracks are detected, repeat the detailed visual 
inspection thereafter at intervals not to exceed 2,000 landings 
until the requirements of paragraph (b) of this AD are accomplished.
    (2) If any crack is detected, prior to further flight, repair it 
in accordance with the AOT. Prior to the accumulation of 15,000 
landings or 20,000 total hours time-in-service, whichever occurs 
first, after the crack is repaired repeat the detailed visual 
inspection at an interval not to exceed 2,000 landings until the 
requirements of paragraph (b) of this AD are accomplished.
    (b) For all airplanes: Perform an eddy current inspection to 
detect cracks of the outer skin of the fuselage at frames 28A and 
30A above stringer 30, in accordance with Airbus Service Bulletin 
A300-53-283, Revision 2, dated March 17, 1994, at the time specified 
in either paragraph (b)(1) or (b)(2) of this AD, as applicable. 
Accomplishment of the eddy current inspection terminates the 
repetitive visual inspection requirements of paragraph (a) of this 
AD.
    (1) For airplanes on which the requirements of paragraph (a) of 
this AD have been initiated: Perform the eddy current inspection 
prior to the accumulation of 2,000 landings since the last 
inspection performed in accordance with paragraph (a) of this AD, or 
within 100 landings after the effective date of this AD, whichever 
occurs later.
    (2) For airplanes other than those identified in paragraph 
(b)(1) of this AD: Perform the eddy current inspection at the later 
of the times specified in paragraph (b)(2)(i) or (b)(2)(ii):
    (i) Prior to the accumulation of 14,100 total landings or 22,000 
total flight hours after the

[[Page 43652]]

effective date of this AD, whichever occurs first; or
    (ii) Within 100 landings after the effective date of this AD.
    (c) If no crack is detected during the eddy current inspection 
required by paragraph (b) of this AD, repeat the eddy current 
inspection thereafter at intervals not to exceed 3,000 landings.
    (d) If any crack is detected during any eddy current inspection 
required by this AD, prior to further flight, repair it in 
accordance with Airbus All Operators Telex 53/90/01, dated April 12, 
1990, or Airbus Service Bulletin A300-53-283, Revision 2, dated 
March 17, 1994. After accomplishing the repair, within 15,000 
landings or 20,000 flight hours after repair, whichever occurs 
first, modify the structure at frames 28A and 30A between stringers 
27 and 30 (left- and right-hand), in accordance with Airbus Service 
Bulletin A300-53-285, Revision 1, dated November 22, 1993. 
Accomplishment of this reinforcement constitutes terminating action 
for this AD.
    (e) Except for airplanes on which the repair required by 
paragraph (d) of this AD has been accomplished: Modify the structure 
at frames 28A and 30A between stringers 27 and 30 (left- and right-
hand), in accordance with Airbus Service Bulletin A300-53-285, 
Revision 1, dated November 22, 1993, at the later of the times 
specified in paragraphs (e)(1) or (e)(2) of this AD. Accomplishment 
of this modification constitutes terminating action for the eddy 
current inspection requirements of paragraph (c) of this AD.
    (1) Prior to the accumulation of 25,000 total landings or 40,000 
total flight hours, whichever occurs first.
    (2) Within 1,000 landings after the effective date of this AD.
    (f) 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, 
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, 
Standardization Branch, ANM-113.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (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.
    (h) The actions shall be done in accordance with one of the 
following Airbus service documents, which contain the specified list 
of effective pages:

----------------------------------------------------------------------------------------------------------------
  Service document referenced and                             Revision level shown                              
                date                        Page No.                on page-              Date shown on page    
----------------------------------------------------------------------------------------------------------------
All Operators Telex (AOT) 53/90/01   1, 2-.................  Original-.............  April 12, 1990.            
 April 12, 1990-.                                                                                               
Service Bulletin A300-53-283,        1-17-.................  2.....................  March 17, 1994.            
 Revision 2, March 17, 1994.                                                                                    
Service Bulletin A300-53-285,        1-3, 6, 13, 14, 18,     1.....................  November 22, 1993. -       
 Revision 1, November 22, 1993.       20, 29-31, 35, 36,                                                        
                                      51, 52, 57, 58, 61,                                                       
                                      62, 71, 72, 75, 76,                                                       
                                      107, 108, 111, 112,                                                       
                                      115-120.                                                                  
  -                                  4, 5, 7-12, 15-17, 19,  Original..............  August 19, 1992.           
                                      21-28, 32-34, 37-50,                                                      
                                      53-56, 59, 60, 63-70,                                                     
                                      73, 74, 77-106, 109,                                                      
                                      110, 113, 114, 121.                                                       
----------------------------------------------------------------------------------------------------------------

    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.
    (i) This amendment becomes effective on September 30, 1996.

    Issued in Renton, Washington, on August 16, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-21458 Filed 8-23-96; 8:45 am]
BILLING CODE 4910-13-U