[Federal Register Volume 62, Number 35 (Friday, February 21, 1997)]
[Rules and Regulations]
[Pages 7926-7928]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-3694]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-65-AD; Amendment 39-9931; AD 97-04-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 and A310 Series 
Airplanes Equipped with Pre-Modification 5844D4829 Rudders

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 A300-600 and A310 series 
airplanes, that currently requires repetitive visual inspections and 
tap tests of the rudder skin panels to detect disbonding; and repairs, 
if necessary. That AD was prompted by reports of weakening of the 
bonding material between the core of the rudder and its inner and outer 
skin, and cracking of the core. This amendment adds repetitive 
elasticity laminate checker (ELCH) inspections of the rudder in place 
of the currently required tap tests. It also requires replacement of 
the rudder with a modified rudder, which will terminate the repetitive 
inspections. The actions specified by this AD are intended to detect 
and prevent disbonding of the rudder, which, if not corrected, could 
reduce the structural integrity of the rudder, and consequently lead to 
a reduction in its ability to sustain limit loads.

DATES: Effective March 28, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 28, 1997.
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 90-12-13, 
amendment 39-6625 (55 FR 23190, June 7, 1990), which is applicable to 
certain Airbus Model A300-600 and A310 series airplanes, was published 
in the Federal Register on October 23, 1996 (61 FR 54955). The action 
proposed to continue to require repetitive visual inspections and tap 
tests of the rudder skin panels to detect disbonding; and repairs, if 
necessary. It also proposed to add repetitive elasticity laminate 
checker (ELCH) inspections of the rudder in place of the currently 
required tap tests. It also proposed to replacement of the rudder with 
a modified rudder, which would terminate the repetitive inspections.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    One commenter supports the proposed AD.

Request To Withdraw the Proposal

    Two commenters request that the FAA withdraw the proposed action. 
These commenters point out that a retrofit campaign was completed in 
1993 on all affected airplanes that were equipped with the pre-
modification 5844 rudders. In effect, that campaign installed the 
proposed terminating action on all airplanes. In light of this, these 
commenters contend that the proposed AD is not necessary.
    The FAA does not concur with the commenters' request to withdraw 
this AD action. The FAA has no evidence that all affected airplanes, 
worldwide, have been modified with the new rudder. This AD will ensure 
that any affected airplane that is imported and placed on the U.S. 
Register in the future, or any airplane that is currenly not operating 
(i.e., is stored) and not equipped with the new rudder, will be 
inspected and modified in accordance with this AD prior to entering 
service.

Request To Correct Service Bulletin Information

    Two commenters point out an error in paragraph (d) of the proposal 
concerning the appropriate source of service information relative to 
the ELCH inspections required on Model A310 series airplanes. The 
proposal indicates that the service bulletin number is A310-55-2008; 
however, the correct number is A310-55-2010.
    The FAA acknowledges that typographical error in proposed paragraph 
(d). The correct service bulletin number was discussed in the preamble 
to the notice and appeared correctly in all other references to it in 
the proposed AD. Paragraph (d) of the final rule has been revised to 
reflect the correct service bulletin number as A310-55-2010.

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 change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any

[[Page 7927]]

operator nor increase the scope of the AD.

Cost Impact

    There are approximately 44 Model A310 and Model A300-600 series 
airplanes of U.S. registry that will be affected by this proposed AD.
    The tap tests that are currently required by AD 90-12-13 take 
approximately 4 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 previously required actions on U.S. operators is 
estimated to be $10,560, or $240 per airplane, per tap test.
    The visual inspections that are currently required by AD 90-12-13 
(and retained in this new AD) 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 of these inspections on U.S. 
operators is estimated to be $2,640, or $60 per airplane, per 
inspection.
    Each ELCH inspection required by this new AD action will take 
approximately 14 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 requirements of this AD on U.S. operators is 
estimated to be $36,960, or $840 per airplane, per inspection.
    The replacement of the rudder that is required by this new AD 
action will take approximately 42 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. The required 
parts will be supplied by the manufacturer at no cost to operators. 
Based on these figures, the cost impact of this required replacement 
action on U.S. operators is estimated to be $110,880, or $2,520 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 
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 39-6625 (55 FR 
23190, June 7, 1990), and by adding a new airworthiness directive (AD), 
amendment 39-9931, to read as follows:

97-04-07 Airbus Industrie: Amendment 39-9931. Docket 96-NM-65-AD. 
Supersedes AD 90-12-13, Amendment 39-6625.

    Applicability: Model A300-600 and A310 series airplanes; 
certificated in any category; equipped with pre-modification 
5844D4829 rudders having the following part numbers:

A5547150000000
A5547150000200
A5547150000400
A5547150000600
A5547150000800
A5547150001000
A5547150001200
A5547150001400

    Note 1: The pre-modification rudders to which this AD applies 
were installed at the time of delivery on Model A300-600 and A310 
series airplanes specified in the effectivity listings of the Airbus 
service bulletins that are referenced in this AD. However, such 
rudders may have been installed after delivery on airplanes other 
than the ones listed in those service bulletins. Therefore, as 
specified by the preceding applicability provision, the operator of 
any Model A300-600 or A310 series airplane equipped with the pre-
modified rudder is required to comply with the requirements of this 
AD.
    Note 2: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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.

    Note 3: The requirements of paragraphs (a) and (b) of this AD 
are restatements of paragraphs A. and B. that appeared in AD 90-12-
13, amendment 39-6625. These paragraphs require no additional action 
by operators who already have initiated the specified actions. (As 
indicated in both paragraphs, these actions are to continue until 
the new actions required by this AD are initiated.)

    To detect and prevent disbonding which, if not corrected, could 
reduce the structural integrity of the rudder, and consequently lead 
to a reduction in its ability to sustain limit loads, accomplish the 
following:
    (a) Visual Inspections (as Required by AD 90-12-13). Within 10 
landings after June 20, 1990 (the effective date of AD 90-12-13, 
amendment 39-6625), perform a visual inspection to detect disbonding 
of the rudder skin panels, left and right, in accordance with Airbus 
All Operators' Telex (AOT) 55/90/01, Revision 1, dated April 27, 
1990. After the effective date of this AD, perform this inspection 
in accordance with Airbus Service Bulletin A300-55-6008 (for Airbus 
Model A300-600 series airplanes), or Airbus Service Bulletin A310-
55-2010 (for Airbus Model A310 series airplanes), both dated 
December 10, 1990, as applicable.
    (1) If no defects are found, repeat the visual inspection 
thereafter at intervals not to exceed 7 days or 50 landings, 
whichever occurs first, until the requirements of paragraph (c) of 
this AD are initiated.
    (2) If defects are found, prior to further flight, perform a tap 
test in accordance with paragraph (b) of this AD.
    (b) Tap Tests (as Required by AD 90-12-13). Within 300 landings 
after June 20, 1990, perform a tap test to determine the extent of 
the damage, in accordance with Airbus AOT 55/90/01, Revision 1, 
dated April 27, 1990.
    (1) If disbonding is less than 100 square cm, repeat the tap 
test of the affected area every 28 days or 200 landings, whichever 
occurs first, until the ELCH inspection requirements of paragraph 
(d) of this AD are initiated. For any signs of additional rudder 
skin panel disbonding, perform drilling procedures in accordance 
with paragraph 4.2.2.3. of the AOT; and thereafter repeat the visual 
inspection of the rudder skin panels

[[Page 7928]]

specified in paragraph (a) of this AD, until the ELCH inspection 
requirements of paragraph (d) of this AD are initiated.
    (2) If disbonding is more than 100 square cm, but less than 
5,000 square cm, repair in accordance with paragraph 4.2.2.3. of the 
AOT. Thereafter, repeat the visual inspection of the rudder skin 
panels in accordance with paragraph (a) of this AD; and perform 
repetitive tap tests of the repaired areas at the following 
intervals; until the visual inspection requirements of paragraph (c) 
of this AD are initiated:
    (i) Perform the tap test of the repaired area every 500 landings 
for disbonding greater than 100 square cm but less than 300 square 
cm;
    (ii) Perform the tap test of the repaired area every 250 
landings for disbonding greater than 300 square cm, but less than 
1,000 square cm;
    (iii) Perform the tap test of the repaired area every 75 
landings for disbonding that is greater than 1,000 square cm, but 
less than 5,000 square cm.
    (3) If disbonding is greater than 5,000 square cm, or if a crack 
is found, prior to further flight, repair in a manner approved by 
the Manager, Standardization Branch, ANM-113, FAA, Transport 
Airplane Directorate.
    (c) New Visual Inspection Requirement. Perform a visual 
inspection of the complete rudder to detect disbonding and cracking 
of the rudder skin panels, left and right, in accordance with Airbus 
Service Bulletin A300-55-6008 (for Airbus Model A300-600 series 
airplanes), or Airbus Service Bulletin A310-55-2010 (for Airbus 
Model A310 series airplanes), both dated December 10, 1990, as 
applicable. Initiation of this inspection constitutes terminating 
action for the requirements of paragraph (a) and specified portions 
of paragraph (b) of this AD.
    (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) Within 7 days or 50 landings after the effective date of 
this AD, whichever is first; or
    (ii) Within 7 days or 50 landings, whichever occurs first after 
the last visual inspection performed in accordance with AD 90-12-13, 
amendment 39-6625.
    (2) If no disbonding or cracking is detected during this 
inspection accomplish the actions specified in paragraphs (c)(2)(i) 
and (c)(2)(ii) of this AD:
    (i) Repeat the visual inspection at intervals not to exceed 7 
days or 50 landings, whichever occurs first, until the initial ELCH 
inspection is accomplished in accordance with paragraph (d) of this 
AD. And
    (ii) After the initial ELCH inspection required by paragraph (d) 
of this AD has been accomplished, repeat these visual inspections 
thereafter at intervals not to exceed 350 landings, in accordance 
with the applicable service bulletin.
    (3) If any disbonding or cracking is detected, prior to further 
flight, conduct an ELCH inspection of the suspected area for signs 
of disbonding, and accomplish follow-on actions in accordance with 
the Flow Chart, Figure 2, of the applicable service bulletin. If the 
confirmed extent of disbonding, however, is greater than 400 square 
cm in Area I, or greater than 800 square cm in Area II, as those 
areas of the rudder are defined in the applicable service bulletin, 
prior to further flight, repair and accomplish subsequent 
inspections in accordance with the requirements of paragraph (d)(3) 
of this AD.
    (d) ELCH Inspections. Within 6 months after the effective date 
of this AD, conduct an initial elasticity laminate checker (ELCH) 
inspection of the complete rudder, in accordance with Airbus Service 
Bulletin A300-55-6008 (for Model A300-600 series airplanes) or 
Airbus Service Bulletin A310-55-2010 (for Model A310 series 
airplanes), both dated December 10, 1990, as applicable. Initiation 
of this inspection constitutes terminating action for the 
requirements of paragraph (a) and specified portions of paragraph 
(b) of this AD.
    (1) If no disbonding or cracking is detected, repeat the ELCH 
inspection at intervals not to exceed 2 years or 3,500 landings, 
whichever occurs first.
    (2) If disbonding or cracking is confirmed by ELCH inspection, 
and the extent of the disbonding is equal to or less than 400 square 
cm in Area I, or equal to or less than 800 square cm in Area II, as 
those areas of the rudder are defined in the applicable service 
bulletin: Prior to further flight, accomplish follow-on actions in 
accordance with Flow Chart, Figure 2, of the applicable service 
bulletin.
    (3) If disbonding or cracking is confirmed by ELCH inspection, 
and the extent of the disbonding is greater than 400 square cm in 
Area I, or greater than 800 square cm in Area II, as those areas of 
the rudder are defined in the applicable service bulletin: Prior to 
further flight, accomplish either paragraph (d)(3)(i) or (d)(3)(ii) 
of this AD:
    (i) Repair in a manner approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate. Thereafter, 
continue to conduct ELCH inspections in a manner and at intervals 
approved by the Manager, Standardization Branch, ANM-113.
    (ii) Replace the rudder in accordance with Airbus Service 
Bulletin A300-55-6010 (for Model A300-600 series airplanes) or 
Airbus Service Bulletin A310-55 2012 (for Model A310 series 
airplanes), both dated April 18, 1991, as applicable. After this 
replacement is accomplished, no further actions are required by this 
AD.
    (e) Terminating Action. Within five years after the effective 
date of this AD, replace the rudder in accordance with Airbus 
Service Bulletin A300-55-6010 (for Model A300-600 series airplanes) 
or Airbus Service Bulletin A310-55 2012 (for Model A310 series 
airplanes), both dated April 18, 1991, as applicable. This 
replacement constitutes terminating action for the inspection 
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, 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Manager, 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 inspections shall be done in accordance with Airbus 
Service Bulletin A300-55-6008, dated December 10, 1990 (for Model 
A300-600 series airplanes); and Airbus Service Bulletin A310-55-
2010, dated December 10, 1990 (for Model A310 series airplanes). The 
rudder replacement shall be done in accordance with Airbus Service 
Bulletin A300-55-6010, dated April 18, 1991 (for Model A300-600 
series airplanes); and Airbus Service Bulletin A310-55 2012, dated 
April 18, 1991 (for Model A310 series airplanes). 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 March 28, 1997.

    Issued in Renton, Washington, on February 7, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-3694 Filed 2-20-97; 8:45 am]
BILLING CODE 4910-13-U