[Federal Register Volume 60, Number 201 (Wednesday, October 18, 1995)]
[Rules and Regulations]
[Pages 53847-53849]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25029]



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 Rules and Regulations
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  Federal Register / Vol. 60, No. 201 / Wednesday, October 18, 1995 / 
Rules and Regulations  

[[Page 53847]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-243-AD; Amendment 39-9395; AD 95-21-09]


Airworthiness Directives; Airbus Model A300 and A300-600 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all Airbus Model A300 series airplanes, that 
currently requires repetitive inspections for cracking of the No. 2 
flap beams, and replacement of the flap beams, if necessary. That AD 
was prompted by reports of cracking of the No. 2 flap beams. This 
amendment provides optional modifications for extending certain 
inspection thresholds, and an optional terminating modification for 
certain inspections. This amendment also expands the applicability of 
the existing AD to include Model A300-600 series airplanes. The actions 
specified by this AD are intended to prevent asymmetry of the flaps due 
to cracking of the No. 2 flap beams.

DATES: Effective November 17, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 17, 1995.

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 85-07-04, 
amendment 39-5027 (49 FR 45755, April 2, 1985), which is applicable to 
all Airbus Model A300 series airplanes, was published in the Federal 
Register on June 9, 1995 (60 FR 30471). That action proposed to 
continue to require repetitive inspections for cracking of the No. 2 
flap beams of Model A300 series airplanes, and replacement of the flap 
beams, if necessary. That action also proposed to require identical 
inspections of Model A300-600 series airplanes. Additionally, that 
action proposed to provide an optional terminating modification for the 
repetitive inspections on the Model 300-600 series airplanes, and 
optional modifications for extending certain inspection thresholds for 
Model A300 series airplanes.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter supports the proposed rule.
    Another commenter also supports the proposed rule, but points out 
that paragraph (d)(3) of the proposed AD contains a typographical 
error. Paragraph (d)(3) should read ``perform the ultrasonic inspection 
required by paragraph (d) of this AD.'' Paragraph (d)(3) currently 
references paragraph (b). The FAA acknowledges a typographical error, 
and has revised paragraph (d)(3) of the final rule accordingly.
    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 change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 23 Model A300 series airplanes and 45 Model 
A300-600 series airplanes of U.S. registry that will be affected by 
this AD.
    The inspections that are currently required by AD 85-07-04, and 
applicable to the Model A300 series airplanes, take approximately 6 
work hours per airplane, per inspection cycle, to accomplish at an 
average labor rate of $60 per work hour. Based on these figures, the 
total cost impact of the actions required by AD 85-07-04 on U.S. 
operators of these airplanes is estimated to be $8,280, or $360 per 
airplane, per inspection cycle.
    The inspections that are required by this new AD, and applicable to 
Model A300-600 series airplanes will take approximately 6 work hours 
per airplane to accomplish, at an average labor rate of $60 per work 
hour. Based on these figures, the total cost impact of these new 
requirements on U.S. operators of these airplane is estimated to be 
$16,200, or $360, per airplane, per inspection cycle.
    The total 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 of a Model A300-600 series airplane elect to 
accomplish the optional terminating action rather than continue the 
repetitive inspections, it would take approximately 55 work hours to 
accomplish it, at an average labor ate of $60 per work hour. Based on 
these figures, the total cost impact of this optional terminating 
action would be $3,300 per airplane.
    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 

[[Page 53848]]
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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-5027 (49 FR 
45755, April 2, 1985), and by adding a new airworthiness directive 
(AD), amendment 39-9395, to read as follows:

95-21-09  Airbus Industrie: Amendment 39-9395. Docket 94-NM-243-AD. 
Supersedes AD 85-07-04, Amendment 39-5027.

    Applicability: All Model A300 and A300-600 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 use the authority 
provided in paragraph (f) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent asymmetry of the No. 2 flaps, accomplish the 
following:

    Note 2: Paragraph (a) of this AD restates the requirement for an 
initial and repetitive inspections contained in paragraph A. of AD 
85-07-04. Therefore, for operators who have previously accomplished 
at least the initial inspection in accordance with AD 85-07-04, 
paragraph (a) of this AD requires that the next scheduled inspection 
be performed within the intervals specified in (a)(1), (a)(2), or 
(a)(3), as applicable, after the last inspection performed in 
accordance with paragraph A. of AD 85-07-04.

    Note 3: Measurement of crack length is performed by measurement 
of the probe displacement (perpendicular to symmetry plane of beam) 
between defect indication appearance and its complete disappearance. 
The bolt hole indication should not be interpreted as an indication 
of a defect. These two indications appear very close together 
because the defects originate from the bolt holes.

    (a) For Model A300 series airplanes: Prior to the accumulation 
of 15,000 total landings, or within the next 120 days after May 9, 
1985 (the effective date of AD 85-07-04, amendment 39-5027), 
whichever occurs later, inspect for cracking of the base steel 
member and light alloy side members of the No. 2 flap beams, left 
hand and right hand, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-116, Revision 6, 
dated July 16, 1993.

    Note 4: Inspections required by paragraph (a) of this AD that 
have been accomplished prior to the effective date of this AD in 
accordance with Airbus Service Bulletin A300-57-116, Revision 1, 
dated August 27, 1983; Revision 2, dated April 24, 1984; Revision 3, 
dated July 20, 1984; Revision 4, dated August 13, 1986; or Revision 
5, dated July 10, 1989; as applicable; are considered acceptable for 
compliance with the applicable action specified in this amendment.

    (1) If no cracking is detected: Except as provided by paragraph 
(c) of this AD, repeat the inspection at intervals not to exceed 
1,700 landings until the requirements of paragraph (b) of this AD 
are accomplished.
    (2) If any crack is detected that is less than or equal to 4 mm: 
Repeat the inspection at intervals not to exceed 250 landings, until 
the requirements of paragraph (b) of this AD are accomplished.
    (3) If any crack is detected that exceeds 4 mm: Prior to further 
flight, replace the flap beam in accordance with the service 
bulletin, and prior to the accumulation of 15,000 flight cycles on 
the replaced flap beam, perform the ultrasonic inspection as 
required by paragraph (b) of this AD.
    (b) For Model A300 series airplanes: Prior to the accumulation 
of 15,000 total landings, or within the next 1,000 landings after 
the effective date of this AD, whichever occurs later, perform an 
ultrasonic inspection to detect cracking of the No. 2 flap beams, in 
accordance with Airbus Service Bulletin No. A300-57-116, Revision 6, 
dated July 16, 1993. Accomplishment of this inspection terminates 
the inspection required by paragraph (a) of this AD.
    (1) If no cracking is detected: Except as provided by paragraph 
(c) of this AD, repeat the ultrasonic inspections thereafter at 
intervals not to exceed 1,700 landings.
    (2) If any crack is detected beyond the bolt hole, and that 
crack is less than or equal to 4 mm in length: Repeat the ultrasonic 
inspections thereafter at intervals not to exceed 250 landings.
    (3) If any crack is detected beyond the bolt hole and that crack 
is greater than 4 mm in length: Prior to further flight, replace the 
flap beam in accordance with the service bulletin, and prior to the 
accumulation of 15,000 flight cycles on the replaced flap beam, 
perform the ultrasonic inspection as required by this paragraph.
    (c) For Model A300 series airplanes: After accomplishing the 
initial inspection required by paragraph (b) of this AD, 
accomplishment of either paragraph (c)(1) or (c)(2) of this AD 
extends the fatigue life of the No. 2 flap track beam as specified 
in those paragraphs, provided that no cracking is detected during 
any inspection required by paragraph (a) or (b) of this AD.
    (1) Removal of any damage and the installation of larger 
diameter bolts on the No. 2 flap track beam (Modification No. 4740), 
in accordance with Airbus Service Bulletin No. A300-57-128, Revision 
3, dated January 26, 1990, extends the interval for the first 
repetitive inspection required by paragraph (b) of this AD from 
1,700 landings to 12,000 landings, provided that Modification No. 
4740 is accomplished prior to the accumulation of 16,700 total 
landings on the flap beams. Following accomplishment of the first 
repetitive inspection, subsequent repetitive inspections shall be 
performed at intervals not to exceed 1,700 landings. Or
    (2) Cold working of the bolt holes and the installation of 
larger diameter bolts on the No. 2 flap track beam (Modification No. 
5815), in accordance with Airbus Service Bulletin No. A300-57-141, 
Revision 7, dated July 16, 1993, extends the interval for the first 
repetitive inspection required by paragraph (b) of this AD from 
1,700 landings to the interval specified in paragraph (c)(2)(i) or 
(c)(2)(ii) of this AD.
    (i) If interference fit bolts that are 15/32-inch in diameter 
are fitted, the interval for the first repetitive inspection 
required by paragraph (b) of this AD is extended to 22,000 landings, 
provided that Modification 5815 is accomplished prior to the 
accumulation of 16,700 total landings on the flap beam. Following 
accomplishment of the first repetitive inspection required by 
paragraph (b) of this AD, subsequent repetitive inspections shall be 
performed at intervals not to exceed 1,700 landings. Or
    (ii) If interference fit bolts that are 7/16- or 3/8-inch in 
diameter are fitted, the interval for the first repetitive 
inspection required by paragraph (b) of this AD is extended to 
33,000 landings, provided that Modification 5815 is accomplished 
prior to the accumulation of 16,700 total landings on the flap beam. 
Following accomplishment of the first repetitive inspection required 
by paragraph (b) of this AD, subsequent repetitive inspections shall 
be performed at intervals not to exceed 1,700 landings.
    (d) For Model A300-600 series airplanes: Prior to the 
accumulation of 15,000 total 

[[Page 53849]]
landings, or within the next 1,000 landings after the effective date of 
this AD, whichever occurs later, perform an ultrasonic inspection to 
detect cracking of the No. 2 flap track beams, in accordance with 
Airbus Service Bulletin No. A300-57-6005, Revision 2, dated December 
16, 1993.
    (1) If no cracking is detected, repeat the ultrasonic 
inspections thereafter at intervals not to exceed 1,700 landings.
    (2) If any crack is detected beyond the bolt hole and that crack 
is less than or equal to 4 mm in length: Repeat the ultrasonic 
inspections thereafter at intervals not to exceed 250 landings.
    (3) If any crack is detected beyond the bolt hole and that crack 
is greater than 4 mm in length: Prior to further flight, replace the 
flap beam in accordance with the service bulletin, and prior to the 
accumulation of 15,000 landings on the replaced flap beam, perform 
the ultrasonic inspection required by paragraph (d) of this AD.
    (e) For Model A300-600 series airplanes: Installation of 
oversized transition fit bolts in cold-worked holes, in accordance 
with Airbus Service Bulletin No. A300-57-6006 (Modification 5815), 
Revision 4, dated July 25, 1994, constitutes terminating action for 
the repetitive inspection requirements of paragraph (d) of this AD, 
provided that no cracking is detected during any inspection required 
by paragraph (d) of this AD, and provided that the installation is 
accomplished prior to the accumulation of 15,000 total landings. If 
any bolt requires oversizing above 7/16-inch diameter during 
accomplishment of this installation, prior to further flight, repair 
in accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate.

    Note 5: If Airbus Service Bulletin No. A300-57-6005, Revision 2, 
dated December 16, 1993, is accomplished concurrently with Airbus 
Service Bulletin No. A300-57-6006 , Revision 3, dated December 16, 
1993 (Modification 5815), the ultrasonic inspection for cracking 
required by paragraph (d) of this AD need not be performed since the 
eddy current inspection detailed for Modification 5815 is more 
comprehensive.

    (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. 
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 6: 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 the following 
Airbus service bulletins, which contain the specified list of 
effective pages:

----------------------------------------------------------------------------------------------------------------
                                                               Revision level -                                 
   Service bulletin referenced and date-        Page No.        shown on page           Date shown on page      
----------------------------------------------------------------------------------------------------------------
A300-57-116, Revision 6, July 16, 1993....              1-11                 6   July 16, 1993.                 
A300-57-128, Revision 3, January 26, 1990.                 1                 3   January 26, 1990.              
                                                         2-5                 1   February 7, 1986.              
                                                        6-14          Original   August 27, 1983.               
A300-57-141, Revision 7, July 16, 1993....              1-24                 7   July 16, 1993.                 
A300-57-6005, Revision 2, December 16,                   1-4                 2   December 16, 1993.             
 1993-.                                                                                                         
                                                      5-7, 9                 1   February 26, 1993.             
                                                           8          Original   August 13, 1986.               
A300-57-6006, Revision 4, July 25, 1994...        1, 2, 5, 7                 4   July 25, 1994.                 
                                               3, 4, 6, 8-20                 3   December 16, 1993.             
----------------------------------------------------------------------------------------------------------------

    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 November 17, 1995.

    Issued in Renton, Washington, on October 3, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-25029 Filed 10-17-95; 8:45 am]
BILLING CODE 4910-13-U