[Federal Register Volume 63, Number 147 (Friday, July 31, 1998)]
[Rules and Regulations]
[Pages 40812-40814]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-20337]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-42-AD; Amendment 39-10680; AD 98-16-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 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 A300-600 series airplanes, that requires 
inspections of the areas behind the scuff plates below the passenger/
crew doors and bulk cargo door 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 behind 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 A300-600 series 
airplanes was published in the Federal Register on January 29, 1997 (62 
FR 4211). 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 proposed to provide 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 comments received.

Clarification of Terminology

    One commenter expresses no objection to the proposed rule, but 
requests that certain terminology in the proposed AD be changed for the 
sake of clarity. The commenter states that the title is not complete, 
since it refers only to inspections of the lower door structure, while 
inspection of the upper door corners is also required. The FAA concurs. 
The FAA infers that the commenter is referring to the Summary section 
of the proposed AD, which states that ``this proposal would require 
inspections of the lower door surrounding structure.'' However, in all 
other sections of the proposed AD, the area to be inspected is 
described as ``the areas behind the scuff plates below the passenger/
crew doors and bulk cargo door,'' in accordance with procedures 
described in Airbus Service Bulletin A300-53-6011, Revision 3, dated 
February 4, 1991. To avoid confusion regarding the area to be inspected 
for cracks and corrosion, the Summary section of the final rule has 
been changed to correspond to the terminology used elsewhere throughout 
the AD.
    The same commenter requests that paragraphs (b) and (d) of the 
proposed AD be changed to refer to the ``fail-safe ring and corner 
strap,'' rather than the existing terminology of ``fail-safe ring and 
corner doubler.'' The commenter states that the term ``corner strap'' 
is used in Airbus Service Bulletin A300-53-6022, dated February 4, 
1991, and in other maintenance documents, rather than ``corner 
doubler.'' The FAA does

[[Page 40813]]

not concur. The FAA has verified that the referenced service bulletin 
uses the term ``corner doubler'' to identify the affected part. 
Therefore, the usage of this terminology has been retained in the final 
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 with the change described 
previously. 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

    The FAA estimates that 35 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 AD on U.S. operators 
is estimated to be $1,470,000, 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 that is 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:

    98-16-05  Airbus: Amendment 39-10680. Docket 96-NM-42-AD.

    Applicability: All Model 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 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 
A300-53-6011, Revision 3, dated February 4, 1991; at the 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 mid and 
aft passenger/crew doors if a steel doubler that covers the entire 
inspection area is installed.
    (1) For airplanes on which Modification 5382S6526 (for forward 
doors) and Modification 5382D4741 (for all other doors) have been 
accomplished prior to delivery of the airplane: Perform the initial 
inspection within 9 years since date of manufacture, or within 1 
year after the effective date of this AD, whichever occurs later.
    (2) For airplanes on which Modification 5382S6526 (for forward 
doors) and Modification 5382D4741 (for all other doors) have not 
been accomplished; and on which the procedures described in Airbus 
Service Information Letter (SIL) A300-53-033, Revision 2 (for all 
doors), dated November 23, 1984, have been accomplished: Perform the 
initial inspection within 5 years after accomplishment of the 
procedures described in the SIL, or within 1 year after the 
effective date of this AD, whichever occurs later.
    (3) For airplanes on which Modification 5382S6526 (for forward 
doors), Modification 5382D4741 (for all other doors), and the 
procedures described in Airbus SIL A300-53-033, Revision 2, dated 
November 23, 1984, have not been accomplished:
    Perform the initial inspection within 4 years since date of 
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 
A300-53-6022, dated February 4, 1991; at the applicable times 
specified in paragraphs (b)(1) and (b)(2) of this AD. Accomplishment 
of these inspections is not required for the mid and aft passenger/
crew doors if a steel doubler that covers the entire inspection area 
is installed.
    (1) For the forward and mid 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: 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 doors: 
Perform the first inspection within 5 years or 6,000 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 6,000 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 A300-53-6022, dated February 
4, 1991. Thereafter, perform the repetitive inspections required by 
paragraph (b) of this AD at the

[[Page 40814]]

applicable times specified in paragraphs (b)(1) and (b)(2) of this 
AD.
    (d) If corrosion is found during any inspection required by 
paragraph (b) of this AD, prior to further flight, repair in 
accordance with Airbus Service Bulletin A300-53-6022, dated February 
4, 1991. Thereafter, perform the repetitive inspections required by 
paragraph (b) of this AD at the applicable times specified in 
paragraphs (d)(1) or (d)(2) of this AD.
    (1) For the upper and lower edges of the fail-safe ring and the 
upper edges of the corner doubler of the aft passenger/crew doors, 
and for the mid passenger/crew door: Inspect at intervals not to 
exceed 5 years or 5,000 landings, whichever occurs first.
    (2) For the forward passenger/crew doors and bulk cargo doors: 
Inspect at intervals not to exceed 5 years.
    (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 A300-53-6018, 
Revision 1, dated April 29, 1992, and at the applicable time 
specified in paragraph (e)(1), (e)(2), (e)(3), or (e)(4) 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 mid 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.
    (4) 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 mid and 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 mid and 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 A300-53-6018, 
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 A300-53-6018, 
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 A300-53-6002, Revision 3, dated 
February 22, 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 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.
    (j) 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.
    (k) Except as provided by paragraph (g)(2) of this AD, the 
actions shall be done in accordance with the following Airbus 
service bulletins, which contain the specified list of effective 
pages:

----------------------------------------------------------------------------------------------------------------
Service bulletin referenced and   Page number shown                                                             
              date                     on page        Revision level shown on page       Date shown on page     
----------------------------------------------------------------------------------------------------------------
A300-53-6022, February 4, 1991.  1-15..............  Original.....................  February 4, 1991.           
A300-53-6002, Revision 3,        1-2, 56, 67-68....  3............................  February 22, 1992.          
 February 22, 1992.                                                                                             
                                 3-26, 31-55, 57-66  1............................  February 4, 1991.           
                                 27-30.............  2............................  May 6, 1991.                
A300-53-6011, Revision 3,        1-17..............  3............................  February 4, 1991.           
 February 4, 1991.                                                                                              
A300-53-6018, Revision 1, April  1, 3-4, 9-14, 17,   1............................  April 29, 1992.             
 29, 1992.                        24, 31-34, 36, 50.                                                            
                                 2, 5-8, 15-16, 18-  Original.....................  February 4, 1991.           
                                  23, 25-30, 35, 37-                                                            
                                  49, 51-65.                                                                    
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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 3: 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.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-20337 Filed 7-30-98; 8:45 am]
BILLING CODE 4910-13-U