[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13489-13491]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6758]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-216-AD; Amendment 39-10398; AD 98-06-20]
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 an existing airworthiness directive 
(AD), applicable to certain Airbus Model A320 series airplanes, that 
currently requires inspections to detect cracking of certain floor 
beams and side box-beams, and repair of cracks; and modification of the 
pressure floor. That AD was prompted by results of a full-scale fatigue 
test. This amendment adds a one-time inspection to verify proper 
clearance between the fasteners of the reinforcement bracket and the 
bellcrank of the free-fall extension system of the main landing gear 
(MLG) and its associated tie rod attachment nut. This amendment also 
adds a requirement for a new improved modification of the pressure 
floor. The actions specified by this AD are intended to prevent reduced 
structural integrity of the fuselage, restricted operation of the MLG 
free-fall system and, consequently, reduced ability to use the MLG 
during an emergency.

DATES: Effective April 24, 1998.
    The incorporation of certain publications, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
April 24, 1998.
    The incorporation by reference of Airbus Industrie Service Bulletin 
A320-53-1024, dated September 23, 1992, as listed in the regulations, 
was approved previously by the Director of the Federal Register as of 
August 23, 1993 (58 FR 39440, July 23, 1993).

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 93-14-04, 
amendment 39-8628 (58 FR 39440, July 23, 1993), which is applicable to 
certain Airbus Model A320 series airplanes, was published as a 
supplemental notice of proposed rulemaking (NPRM) in the Federal 
Register on March 12, 1997 (62 FR 11388). The action proposed to 
continue to require inspections to detect cracking of the floor beams 
and the side box-beams, and repair of cracks. The action also proposed 
to add a one-time inspection to verify proper clearance between the 
fasteners of the reinforcement bracket and the bellcrank of the free-
fall extension system of the main landing gear (MLG) and its associated 
tie rod attachment nut. In addition, the action proposed to add a 
requirement for a new improved modification of the pressure floor.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter requests that paragraph (c)(1)(ii) of the 
supplemental NPRM be revised to include an option to rework the 
bellcrank just like paragraph (c)(1)(iii)(B) of the supplemental NPRM. 
The commenter points out that the Direction Generale de l'Aviation 
Civile (DGAC), which is the airworthiness authority for France, has 
included this rework option in its revised French airworthiness 
directive (CN) 96-053-77(B)R1, dated June 5, 1996.
    The FAA concurs. The FAA has reviewed the subject French 
airworthiness directive, and has revised paragraph (c)(1)(ii) of this 
final rule to include an option to rework the bellcrank lever and 
fasteners, and reinstall the reinforcement bracket fasteners, which is 
identical to the requirements of paragraph (c)(1)(iii)(B) of the AD.

Conclusion

    After careful review of the available data, including the comment 
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.

Cost Impact

    There are approximately 24 Airbus Model A320 series airplanes of 
U.S. registry that will be affected by this AD.
    The inspections that are currently required by AD 93-14-04 take 
approximately 37 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 currently required inspections on U.S. operators is 
estimated to be $53,280, or $2,220 per airplane.
    The new inspection that is required by this AD action will take 
approximately 11 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 inspection required by this AD on U.S. operators is 
estimated to be $15,840, or $660 per airplane.
    The new modification that is required by this AD action will take 
approximately 142 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will be supplied by the 
manufacturer at no cost to the operators. Based on these figures, the 
cost impact of the modification required by this AD on U.S. operators 
is estimated to be $204,480, or $8,520 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

[[Page 13490]]

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 39-8628 (58 FR 
39440, July 23, 1993), and by adding a new airworthiness directive 
(AD), amendment 39-10398, to read as follows:

98-06-20  Airbus Industrie: Amendment 39-10398. Docket 95-NM-216-AD. 
Supersedes AD 93-14-04, Amendment 39-8628.

    Applicability: Model A320 series airplanes, manufacturer's 
serial numbers 002 through 008 inclusive, 010 through 078 inclusive, 
and 080 through 107 inclusive; 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.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of the fuselage, 
restricted operation of the main landing gear (MLG) free-fall 
system, and, consequently, reduced ability to use the MLG during an 
emergency, accomplish the following:
    (a) Prior to the accumulation of 12,000 total landings, or 
within 6 months after August 23, 1993 (the effective date of AD 93-
14-04, amendment 39-8628), whichever occurs later, accomplish the 
requirements of paragraphs (a)(1) and (a)(2) of this AD, in 
accordance with Airbus Service Bulletin A320-53-1024, dated 
September 23, 1992, or Revision 1, dated March 31, 1994. As of the 
effective date of this new AD, only Revision 1 of this service 
bulletin shall be used.
    (1) Conduct an eddy current inspection to detect cracking around 
the fastener/bolt holes at the top horizontal flange of the floor 
beams and side box-beams, at the two sides of the pressure floor, 
and at the vertical integral stiffener of the side box-beams; and
    (2) Conduct a detailed visual inspection to detect cracking 
around the fastener/bolt holes at the fillet radius and riveted area 
of the top outboard flange of the side box-beam, and at the flange-
corner radius of the slanted inboard flange of the side box-beam and 
fittings.
    (b) If any crack is detected during the inspections required by 
paragraph (a) of this AD, prior to further flight, repair the crack 
in accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate.
    (c) For airplanes on which the modification specified in Airbus 
Service Bulletin A320-53-1023, dated September 23, 1992, as amended 
by Service Bulletin Change Notice 0A, dated January 20, 1993; 
Revision 1, dated March 23, 1993; Revision 2, dated October 22, 
1993; Revision 3, dated March 18, 1994; Revision 4, dated September 
30, 1994; Revision 5, dated February 28, 1995; or Revision 6, dated 
September 4, 1995; has been accomplished: Accomplish paragraphs 
(c)(1) and (c)(2) of this AD.
    (1) Prior to the accumulation of 1,000 landings after the 
effective date of this AD, perform a one-time inspection to verify 
proper clearance between the fasteners of the reinforcement bracket 
and the bellcrank of the free-fall extension system of the MLG and 
its associated tie rod attachment nut, in accordance with Airbus All 
Operators Telex (AOT) 53-08, Revision 01, dated January 15, 1996.
    (i) If the minimum clearance is greater than 3 mm (0.118 inch) 
and no evidence of interference is detected, within 60 months 
following accomplishment of the inspection required by paragraph 
(c)(1) of this AD, reinstall the reinforcement bracket fasteners in 
accordance with Airbus Service Bulletin A320-53-1023, Revision 7, 
dated November 3, 1995.
    (ii) If the minimum clearance is 3 mm (0.118 inch) or less, and 
no evidence of interference is detected, within 18 months following 
accomplishment of the inspection required by paragraph (c)(1) of 
this AD, accomplish either paragraph (c)(1)(ii)(A) or (c)(1)(ii)(B) 
of this AD.
    (A) Reinstall the reinforcement bracket fasteners in accordance 
with Airbus Service Bulletin A320-53-1023, Revision 7, dated 
November 3, 1995; or
    (B) Rework the bellcrank lever and fasteners in accordance with 
Airbus AOT 53-08, Revision 01, dated January 15, 1996. Within 60 
months following accomplishment of the rework, reinstall the 
reinforcement bracket fasteners in accordance with Airbus Service 
Bulletin A320-53-1023, Revision 7, dated November 3, 1995.
    (iii) If any interference is detected, prior to further flight, 
accomplish either paragraph (c)(1)(iii)(A) or (c)(1)(iii)(B) of this 
AD.
    (A) Reinstall the reinforcement bracket fasteners in accordance 
with Airbus Service Bulletin A320-53-1023, Revision 7, dated 
November 3, 1995; or
    (B) Rework the bellcrank lever and fasteners in accordance with 
Airbus AOT 53-08, Revision 01, dated January 15, 1996. Within 60 
months following accomplishment of the rework, reinstall the 
reinforcement bracket fasteners in accordance with Airbus Service 
Bulletin A320-53-1023, Revision 7, dated November 3, 1995.
    (2) Prior to the accumulation of 24,000 total landings, or 
within 6 months after the effective date of this AD, whichever 
occurs later, modify the pressure floor at section 15 of the 
fuselage in accordance with Airbus Service Bulletin A320-53-1023, 
Revision 7, dated November 3, 1995. Accomplishment of the 
modification terminates the requirements of this AD.
    (d) For airplanes on which the modification specified in Airbus 
Service Bulletin A320-53-1023, dated September 23, 1992, as amended 
by Service Bulletin Change Notice 0A, dated January 20, 1993; 
Revision 1, dated March 23, 1993; Revision 2, dated October 22, 
1993; Revision 3, dated March 18, 1994; Revision 4, dated September 
30, 1994; Revision 5, dated February 28, 1995; or Revision 6, dated 
September 4, 1995; has not been accomplished: Prior to the 
accumulation of 18,000 total landings, or within 6 months after the 
effective date of this AD, whichever occurs later, modify the 
pressure floor at section 15 of the fuselage in accordance with 
Airbus Service Bulletin A320-53-1023, Revision 7, dated November 3, 
1995. Accomplishment of the modification terminates the requirements 
of this AD.
    (e) Accomplishment of the modification of the pressure floor at 
section 15 of the fuselage in accordance with Airbus Service 
Bulletin A320-53-1023, Revision 7, dated November 3, 1995, 
constitutes terminating action for the requirements 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, 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.


[[Page 13491]]


    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.

    (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 Airbus Service 
Bulletin A320-53-1024, dated September 23, 1992; Airbus Service 
Bulletin A320-53-1024, Revision 1, dated March 31, 1994; Airbus All 
Operators Telex (AOT) 53-08, Revision 01, dated January 15, 1996; 
and Airbus Service Bulletin A320-53-1023, Revision 7, dated November 
3, 1995; as applicable. Revision 7 of Airbus Service Bulletin A320-
53-1023 contains the following list of effective pages:

------------------------------------------------------------------------
                                  Revision                              
                                   level                                
            Page No.              shown on       Date shown on page     
                                    page                                
------------------------------------------------------------------------
1, 15-55.......................          7  November 3, 1995.           
2-14...........................          6  September 4, 1995.          
------------------------------------------------------------------------

    The incorporation by reference of Airbus Industrie Service 
Bulletin A320-53-1024, dated September 23, 1992, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of 
August 23, 1993 (58 FR 39440, July 23, 1993). The incorporation by 
reference of the remainder of the service documents listed above is 
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 directives (CN's) 92-205-033(B)R1, dated June 22, 
1994, and 96-053-077(B)R1, dated June 5, 1996.

    (i) This amendment becomes effective on April 24, 1998.

    Issued in Renton, Washington, on March 10, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-6758 Filed 3-19-98;8:45 am]
BILLING CODE 4910-13-U