[Federal Register Volume 63, Number 147 (Friday, July 31, 1998)]
[Rules and Regulations]
[Pages 40819-40821]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-20338]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-44-AD; Amendment 39-10682; AD 98-16-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A310 series airplanes, that requires 
inspections of the lower door surrounding structure to detect cracks 
and corrosion, and repair, if necessary. This amendment also requires 
inspections to detect cracking of the holes of the corner doublers, the 
fail-safe ring, and the door frames of the door structures; and repair, 
if necessary. In addition, this amendment provides for optional 
terminating action for certain inspections. This amendment is prompted 
by reports indicating that corrosion was found between the scuff plates 
at exit and cargo doors, and fatigue cracks originated from certain 
fastener holes located in adjacent structure. The actions specified by 
this AD are intended to detect and correct such corrosion and fatigue 
cracking, which could result in reduced structural integrity of the 
door surroundings.

DATES: Effective September 4, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 4, 1998.

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) to include an airworthiness 
directive (AD) that is applicable to all Airbus Model A310 series 
airplanes was published in the Federal Register on January 29, 1997 (62 
FR 4208). That action proposed to require inspections of the lower door 
surrounding structure to detect cracks and corrosion, and repair, if 
necessary. That action also proposed to require inspections to detect 
cracking of the holes of the corner doublers, the fail-safe ring, and 
the door frames of the door structures; and repair, if necessary. In 
addition, that action also provides for optional terminating action for 
certain inspections.

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.

Request to Mandate Optional Terminating Action

    One commenter supports the proposed AD, but states that the FAA 
should not allow operators to forego accomplishment of the terminating 
action in lieu of repetitive inspections. The commenter states that 
allowing the terminating action to be optional will ``allow airplanes 
to operate that have cracks in the door frames that will be more 
subject to failure in the event of an accident.'' Additionally, the 
commenter notes that accident history has shown that there is already a 
significant problem with the emergency operation of doors following 
minor fuselage deformation, even though this is a requirement under 
section 25.783(c) of the Federal Aviation Regulations [14 CFR 
25.783(c)].
    The FAA does not concur with the request to mandate the terminating 
action. As stated in the preamble to the NPRM, the FAA considers 
certain criteria in allowing repetitive inspections of the affected 
area to be permitted to continue, and has determined that, in this 
case, mandating the terminating action is not necessary in order to 
adequately address the identified unsafe condition. The FAA has 
determined that the inspection intervals required by the AD were 
established to detect any cracking before it becomes critical to the 
airplane structure. Additionally, even if small cracks exist that are 
not detected by the inspections at the intervals required by this AD, 
the cracks will not adversely affect the structure of the door under 
ultimate loads, and such cracking is unlikely to result in interference 
with the operation of emergency exits. Therefore, no change to the 
final rule is necessary.

Explanation of Change Made to This Final Rule

    Paragraphs (b), (c), and (d) of the final rule have been revised to 
cite Revision 02 of Airbus Service Bulletin A310-53-2041, dated July 2, 
1996, for accomplishment of certain actions. Revision 02 contains no 
substantive differences from Revision 1 of the service bulletin 
(Revision 1 was cited as the appropriate source of service information 
in the proposed AD). However, Revision 02 contains an additional 
description of the inspections required by paragraph (b) of the AD. A 
``NOTE'' has been added to the final rule to give credit to operators 
that may have previously accomplished the required actions in 
accordance with Revision 1 of the service bulletin.

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

[[Page 40820]]

operator nor increase the scope of the AD.

Cost Impact

    The FAA estimates that 33 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 700 work hours per 
airplane to accomplish the required inspections (including access and 
close-up), and that the average labor rate is $60 per work hour. Based 
on these figures, the cost impact of the required inspections on U.S. 
operators is estimated to be $1,386,000, or $42,000 per airplane.
    The cost impact figure discussed above is 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 elect to accomplish the optional terminating 
action provided by this AD action, it will take approximately 147 work 
hours to accomplish it, at an average labor rate of $60 per work hour. 
The cost of required parts will be approximately $5,581 per airplane. 
Based on these figures, the cost impact of the optional terminating 
action will be $14,401 per airplane.

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 adding the following new 
airworthiness directive:

98-16-06  Airbus Industrie: Amendment 39-10682. Docket 96-NM-44-AD.

    Applicability: All Model A310 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 (i) 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 detect and correct corrosion behind the scuff plates at exit 
and cargo doors, and fatigue cracking in certain fastener holes 
located in adjacent structure, which could result in reduced 
structural integrity of the door surroundings, accomplish the 
following:
    (a) Perform an initial inspection of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with Airbus Service Bulletin 
A310-53-2030, Revision 5, dated March 6, 1991; at the applicable 
time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD. If 
any crack or corrosion is found during this inspection, prior to 
further flight, repair in accordance with the service bulletin. 
Accomplishment of this inspection is not required for the aft 
passenger/crew doors if a steel doubler that covers the entire 
inspection area is installed.
    (1) For any door on which Modification 5382 has been 
accomplished: Perform the initial inspection within 9 years since 
airplane manufacture, or within 1 year after the effective date of 
this AD, whichever occurs later.
    (2) For any door on which Modification 5382 has not been 
accomplished, and on which the procedures described in Airbus 
Service Bulletin A310-53-2004, Revision 2, dated June 17, 1985, or 
Airbus Service Information Letter 53-033, Revision 2, dated November 
23, 1984, have been accomplished: Perform the initial inspection 
within 5 years since airplane manufacture, or within 1 year after 
the effective date of this AD, whichever occurs later.
    (3) For any door on which Modification 5382 has not been 
accomplished, and on which the procedures described in Airbus 
Service Bulletin A310-53-2004, Revision 2, dated June 17, 1985, or 
Airbus Service Information Letter 53-033, Revision 2, dated November 
23, 1984, have not been accomplished: Perform the initial inspection 
within 4 years since airplane manufacture, or within 1 year after 
the effective date of this AD, whichever occurs later.
    (b) Perform repetitive inspections of the areas behind the scuff 
plates below the passenger/crew doors and bulk cargo door to detect 
cracks and corrosion, in accordance with Airbus Service Bulletin 
A310-53-2041, Revision 02, dated July 2, 1996; at the applicable 
times specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD. 
Accomplishment of these inspections is not required for the aft 
passenger/crew doors if a steel doubler that covers the entire 
inspection area is installed.
    (1) For the forward passenger/crew doors, the bulk cargo door, 
and the aft passenger/crew doors, except the upper and lower edges 
of the fail-safe ring and the upper edges of the corner doubler, on 
all Model A310-200 and -300 series airplanes: Perform the first 
inspection within 5 years after accomplishing the inspection 
required by paragraph (a) of this AD; and repeat the inspection 
thereafter at intervals not to exceed 5 years.
    (2) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew door on 
all Model A310-200 series airplanes: Perform the first inspection 
within 5 years or 12,000 landings after accomplishing the inspection 
required by paragraph (a) of this AD, whichever occurs first; and 
repeat the inspection thereafter at intervals not to exceed 5 years 
or 12,000 landings, whichever occurs first.
    (3) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew door on 
all Model A310-300 series airplanes: Perform the first inspection 
within 5 years or 7,000 landings after accomplishing the inspection 
required by paragraph (a) of this AD, whichever occurs first; and 
repeat the inspection thereafter at intervals not to exceed 5 years 
or 7,000 landings, whichever occurs first.
    (c) If any crack is found during any inspection required by 
paragraph (b) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A310-53-2041, Revision 02, 
dated July 2, 1996. Thereafter, perform the repetitive inspections 
required by paragraph (b) of this AD at the applicable times 
specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD.
    (d) If any corrosion is found during any inspection required by 
paragraph (b) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A310-53-2041, Revision 02, 
dated July 2, 1996. Thereafter, perform the repetitive

[[Page 40821]]

inspections required by paragraph (b) of this AD at the applicable 
time specified in paragraph (d)(1) or (d)(2) of this AD.
    (1) For Model A310-200 series airplanes: Inspect at intervals 
not to exceed 5 years or 9,600 landings, whichever occurs first.
    (2) For Model A310-300 series airplanes: Inspect at intervals 
not to exceed 5 years or 5,600 landings, whichever occurs first.
    Note 2: Accomplishment of the actions required by paragraph (b), 
(c), or (d) of this AD in accordance with Airbus Service Bulletin 
A310-53-2041, Revision 1, dated March 6, 1991, prior to the 
effective date of this AD, is acceptable for compliance with that 
paragraph.
    (e) Perform an inspection to detect cracking of the holes of the 
corner doublers, the fail-safe ring, and the door frames of the 
left-and right-hand forward, mid, and aft passenger/crew door 
structures, in accordance with Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992, and at the applicable times 
specified in paragraphs (e)(1), (e)(2), and (e)(3) of this AD.
    (1) For the upper corners of the forward doors: Inspect prior to 
the accumulation of 20,000 total landings, or within 2,000 landings 
after the effective date of this AD, whichever occurs later.
    (2) For the lower corners of the forward doors: Inspect prior to 
the accumulation of 20,000 total landings, or within 4,000 landings 
after the effective date of this AD, whichever occurs later.
    (3) For the upper and lower corners of the aft doors, and for 
the parts underneath the corners of the upper door frames: Inspect 
prior to the accumulation of 20,000 total landings, or within 4,000 
landings after the effective date of this AD, whichever occurs 
later.
    (f) Repeat the inspections required by paragraph (e) of this AD 
at the applicable times specified in paragraphs (f)(1), (f)(2), 
(f)(3), (f)(4), and (f)(5).
    (1) For the upper corners of the forward doors: Inspect at 
intervals not to exceed 6,000 landings.
    (2) For the lower corners of the forward doors: Inspect at 
intervals not to exceed 10,000 landings.
    (3) For the upper and lower corners of the aft doors on which an 
inspection required by paragraph (e) of this AD was accomplished 
using a Roto test technique: Inspect at intervals not to exceed 
8,000 landings.
    (4) For the upper and lower corners of the aft doors on which an 
inspection required by paragraph (e) of this AD was accomplished 
using an X-ray technique: Inspect at intervals not to exceed 3,500 
landings.
    (5) For the areas around the fasteners in the vicinity of 
stringer 12 on the upper door frames of the aft doors on which an 
inspection required by paragraph (e) of this AD was accomplished 
using a visual technique: Inspect at intervals not to exceed 6,900 
landings.
    (g) If any crack is found during any inspection required by 
paragraph (e) or (f) of this AD: Prior to further flight, accomplish 
the requirement of paragraph (g)(1) or (g)(2) of this AD, as 
applicable.
    (1) If any crack is found, and the crack can be eliminated using 
the method specified in Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992: Prior to further flight, repair 
the crack in accordance with that service bulletin.
    (2) If any crack is found, and the crack cannot be eliminated 
using the method specified in Airbus Service Bulletin A310-53-2037, 
Revision 1, dated April 29, 1992: Prior to further flight, repair 
the crack in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate.
    (h) Modification of the passenger/crew door frames in accordance 
with Airbus Service Bulletin A310-53-2017, Revision 7, dated 
February 25, 1992, constitutes terminating action for the repetitive 
inspections required by paragraph (f) of this AD.
    (i) 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. 
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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (j) Special flight permits may be issued in accordance with 
Secs. 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.
    (k) Except as provided by paragraphs (g)(2) and (h), the actions 
shall be done in accordance with the following Airbus service 
bulletins, which contain the specified effective pages:

----------------------------------------------------------------------------------------------------------------
Service bulletin referenced and   Page number shown                                                             
              date                     on page        Revision level shown on page       Date shown on page     
----------------------------------------------------------------------------------------------------------------
A310-53-2030, Revision 5, March  1-2, 4-5, 7-9, 14.  5............................  March 6, 1991.              
 6, 1991.                                                                                                       
                                 3, 6, 10-13,15-17.  4............................  December 5, 1990.           
A310-53-2041, Revision 02, July  1-21..............  02...........................  July 2, 1996.               
 2, 1996.                                                                                                       
A300-53-2037, Revision 1, April  1, 4, 6, 11-15,     1............................  April 29, 1992.             
 29, 1992.                        18, 29, 39-44,                                                                
                                  46, 57.                                                                       
                                 2-3, 5, 7-10, 16-   Original.....................  December 11, 1990.          
                                  17, 19-28, 30-38,                                                             
                                  45, 47-56, 58-60.                                                             
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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 4: The subject of this AD is addressed in French 
airworthiness directive 91-132-124(B), dated June 26, 1991, as 
amended by a Correction, dated August 21, 1991.

    (l) This amendment becomes effective on September 4, 1998.

    Issued in Renton, Washington, on July 24, 1998.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-20338 Filed 7-30-98; 8:45 am]
BILLING CODE 4910-13-U