AD Amdt-39-10032

[Federal Register Volume 62, Number 100 (Friday, May 23, 1997)]
[Rules and Regulations]
[Pages 28325-28328]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 97-12859]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-43-AD; Amendment 39-10032; AD 97-11-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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[[Page 28326]]

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A300 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 will also require 
modification of the passenger/crew door frames, which, when 
accomplished, terminates 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 June 27, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 27, 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: Charles Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2589; 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 series 
airplanes was published in the Federal Register on January 29, 1997 (62 
FR 4213). 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 require modification of the 
passenger/crew door frames, which, when accomplished, constitutes 
terminating action for certain inspections.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 4 Airbus Model A300 series airplanes of U.S. 
registry will be affected by this AD.
    It will take approximately 700 work hours per airplane to 
accomplish the required inspections, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of the required 
inspections on U.S. operators is estimated to be $168,000, or $42,000 
per airplane.
    The FAA estimates that it will take approximately 330 work hours 
per airplane to accomplish the required modification, and that the 
average labor rate is $60 per work hour. Required parts will cost 
approximately $1,055 per airplane. Based on these figures, the cost 
impact of the required modification on U.S. operators is estimated to 
be $83,420, or $20,855 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 adding the following new 
airworthiness directive:

97-11-03  Airbus: Amendment 39-10032. Docket 96-NM-43-AD.

    Applicability: All Model A300 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 
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 (h) 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 
A300-53-204, Revision 6, dated October 11, 1993; at the applicable 
time specified in paragraph (a)(1), (a)(2), (a)(3), or (a)(4) of 
this AD. If any crack or corrosion is found during this inspection, 
prior to further flight, repair in accordance

[[Page 28327]]

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 Modifications 5382S6526 (for forward 
doors), 3690S4613 (for forward doors), and 5382D4741 (for all other 
doors) have been accomplished prior to delivery of the airplane: 
Perform the initial inspection within 9 years since manufacture, or 
within 1 year after the effective date of this AD, whichever occurs 
later.
    (2) For airplanes on which the procedures described in Airbus 
Service Information Letter (SIL) A300-53-033, Revision 2 (for all 
doors), dated November 23, 1984; or Airbus Service Bulletin A300-53-
169 (for forward doors), Revision 2, dated May 14, 1985; have been 
accomplished: Perform the initial inspection within 5 years after 
accomplishment of the SIL or the service bulletin, or within 1 year 
after the effective date of this AD, whichever occurs later.
    (3) For airplanes on which the procedures described in Airbus 
Service Bulletin A300-53-116 (for all doors), Revision 4, dated June 
30, 1983, have been accomplished: Perform the initial inspection 
within 2 years after accomplishment of the procedures in accordance 
with that service bulletin, or within 1 year after the effective 
date of this AD, whichever occurs later.
    (4) For airplanes on which Modifications 5382S6526 (for forward 
doors), 3690S4613 (for forward doors), and 5382D4741 (for all other 
doors); and the procedures described in Airbus Service Bulletin 
A300-53-116, Revision 4, dated June 30, 1983; or Service Information 
Letter (SIL) A300-53-033, Revision 2, dated November 23, 1984; have 
not been accomplished: Perform the initial inspection within 1 year 
after the effective date of this AD.
    (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 
A300-53-233, Revision 1, dated April 18, 1991, at the applicable 
times specified in paragraphs (b)(1) and (b)(2) of this AD. 
Accomplishment of these 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 the forward and mid passenger/crew doors, the bulk cargo 
doors, the emergency exits, and the aft passenger/crew doors, except 
for 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 following the immediately preceding inspection.
    (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 10,000 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 10,000 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 A300-53-233, Revision 1, 
dated April 18, 1991. Thereafter, perform the repetitive inspections 
required by paragraph (b) of this AD at the applicable times 
specified in paragraphs (b)(1) and (b)(2) 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 A300-53-233, Revision 1, 
dated April 18, 1991. Thereafter, perform the repetitive inspections 
required by paragraph (b) of this AD at the applicable times 
specified in paragraphs (d)(1) and (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 doors: Inspect at intervals not to 
exceed 5 years or 8,000 landings, whichever occurs first.
    (2) For the forward passenger/crew doors, bulk cargo door, and 
emergency exits: Inspect at intervals not to exceed 5 years.
    (e) Perform inspections 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 A300-53-227, 
Revision 1, dated April 29, 1992. Perform the inspections at the 
times specified in paragraphs (e)(1), (e)(2), and (e)(3) of this AD, 
as applicable. If any cracking is found, prior to further flight, 
repair in accordance with the service bulletin; or, if cracks cannot 
be eliminated in accordance with the service bulletin, repair in 
accordance with a method approved by the Manager, Standardization 
Branch, ANM-113, FAA, Transport Airplane Directorate.
    (1) Except as provided by paragraph (e)(2) of this AD, for the 
left- and right-hand forward and mid passenger/crew door structures 
of all airplanes: Inspect at the time specified in paragraph 
(e)(1)(i), (e)(1)(ii), (e)(1)(iii), or (e)(1)(iv) of this AD, as 
applicable.
    (i) For airplanes that have accumulated less than 20,000 total 
landings as of the effective date of this AD: Inspect prior to the 
accumulation of 20,000 total landings, or within 1,250 landings 
after the effective date of this AD, whichever occurs later.
    (ii) For airplanes that have accumulated 20,000 total landings 
or more, but less than 21,000 landings as of the effective date of 
this AD: Inspect prior to the accumulation of 21,000 total landings, 
or within 1,000 landings after the effective date of this AD, 
whichever occurs later.
    (iii) For airplanes that have accumulated 21,000 total landings 
or more, but less than 22,000 landings as of the effective date of 
this AD: Inspect prior to the accumulation of 22,000 total landings, 
or within 500 landings after the effective date of this AD, 
whichever occurs later.
    (iv) For airplanes that have accumulated 22,000 total landings 
or more as of the effective date of this AD: Inspect within 250 
landings after the effective date of this AD.
    (2) For the left-hand mid passenger/crew door structures of 
Model A300 C4 and F4 series airplanes: Inspect at the time specified 
in paragraph (e)(2)(i), (e)(2)(ii), (e)(2)(iii), or (e)(2)(iv) of 
this AD, as applicable.
    (i) For airplanes that have accumulated less than 12,000 total 
landings as of the effective date of this AD: Inspect prior to the 
accumulation of 12,000 total landings, or within 1,250 landings 
after the effective date of this AD, whichever occurs later.
    (ii) For airplanes that have accumulated 12,000 total landings 
or more, but less than 13,000 landings as of the effective date of 
this AD: Inspect prior to the accumulation of 13,000 total landings, 
or within 1,000 landings after the effective date of this AD, 
whichever occurs later.
    (iii) For airplanes that have accumulated 13,000 total landings 
or more, but less than 14,000 landings as of the effective date of 
this AD: Inspect prior to the accumulation of 14,000 total landings, 
or within 500 landings after the effective date of this AD, 
whichever occurs later.
    (iv) For airplanes that have accumulated 14,000 total landings 
or more as of the effective date of this AD: Inspect within 250 
landings after the effective date of this AD.
    (3) For the left-and right-hand aft passenger/crew door 
structures of all airplanes: Inspect prior to the accumulation of 
24,000 total landings, or within 250 landings after the effective 
date of this AD, whichever occurs later.
    (f) Repeat the inspections required by paragraph (e) of this AD 
at the times specified in paragraphs (f)(1), (f)(2), (f)(3), (f)(4), 
(f)(5), (f)(6), (f)(7), (f)(8), (f)(9), and (f)(10), as applicable, 
until the modification required by paragraph (g) of this AD is 
accomplished.
    (1) For the forward passenger/crew door structure of airplanes 
on which Airbus
    Modification No. 1282/S1862 has not been accomplished: Inspect 
at the intervals specified in paragraphs (f)(1)(i) and (f)(1)(ii), 
as applicable.
    (i) For the upper corners of the door structure: At intervals 
not to exceed 4,000 landings.
    (ii) For the lower corners of the door structure: At intervals 
not to exceed 7,500 landings.
    (2) For the forward passenger/crew door structure of airplanes 
on which Airbus Modification No. 1282/S1862 has been accomplished: 
Inspect at the intervals specified in paragraphs (f)(2)(i) and 
(f)(2)(ii), as applicable.
    (i) For the upper corners of the door structure: At intervals 
not to exceed 6,000 landings.
    (ii) For the lower corners of the door structure: At intervals 
not to exceed 10,000 landings.
    (3) For the forward passenger/crew door structure of the 
airplane having manufacturer's serial number 063, on which Airbus 
Modification No. 1282/S1862 has been accomplished partially: Inspect 
at the intervals specified in paragraph (f)(3)(i) or (f)(3)(ii), as 
applicable.
    (i) For the upper corners of the door structure: At intervals 
not to exceed 4,000 landings.
    (ii) For the lower corners of the door structure: At intervals 
not to exceed 7,500 landings.

[[Page 28328]]

    (4) For the left-and right-hand mid passenger/crew door 
structure on Model A300 B1, B2, and B4 series airplanes; and for the 
right-hand mid passenger/crew door structure on Model A300 C4 and F4 
series airplanes; 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.
    (5) For the left-and right-hand mid passenger/crew door 
structure on Model A300 B1, B2, and B4 series airplanes; and for the 
right-hand mid passenger/crew door structure on Model A300 C4 and F4 
series airplanes; 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.
    (6) For the left-hand mid passenger/crew door structure on Model 
A300 C4 and F4 series airplanes on which an inspection required by 
paragraph (e) of this AD was accomplished using a Roto test 
technique: Inspect at intervals not to exceed 5,200 landings.
    (7) For the left-hand mid passenger/crew door structure on Model 
A300 C4 and F4 series airplanes on which an inspection required by 
paragraph (e) of this AD was accomplished using an X-ray technique: 
Inspect at intervals not to exceed 2,300 landings.
    (8) For the aft passenger/crew door structure 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.
    (9) For the aft passenger/crew door structure 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.
    (10) For the areas around the fasteners in the vicinity of 
stringer 12 on the aft passenger/crew door structure 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) Prior to the accumulation of 20,000 total landings, or 
within 1 year after the effective date of this AD, whichever occurs 
later: Modify the passenger/crew door structures in accordance with 
Airbus Service Bulletin A300-53-192, Revision 7, dated July 13, 
1992. Accomplishment of this modification constitutes terminating 
action for the repetitive inspections required by paragraph (f) of 
this AD.
    (h) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (i) 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.
    (j) The inspections and repairs shall be done in accordance with 
the following Airbus service bulletins, which contain the specified 
list of effective pages:

----------------------------------------------------------------------------------------------------------------
  Service bulletin referenced and                          Revision level shown                                 
               date                       Page No.               on page                Date shown on page      
----------------------------------------------------------------------------------------------------------------
A300-53-204, Revision 6, October    1, 2, 11, 12........  6....................  October 11, 1993.              
 11, 1993.                                                                                                      
                                    3-5, 7-10, 13-17....  3....................  September 25, 1990.            
                                    6...................  4....................  April 18, 1991.                
A300-53-233, Revision 1, April 18,  1, 6................  1....................  April 18, 1991.                
 1991.                                                                                                          
                                    2-5, 7-17...........  Original.............  December 5, 1990.              
A300-53-227, Revision 1, April 29,  1-4, 6, 7, 11, 12,    1....................  April 29, 1992.                
 1992.                               16-18, 37-50, 57,                                                          
                                     58, 62, 64, 67, 68,                                                        
                                     91, 92, 97, 98,                                                            
                                     110, 116.                                                                  
                                    5, 8-10, 13-15, 19-   Original.............  December 3, 1990.              
                                     36, 51-56, 59-61,                                                          
                                     63, 65, 66, 69-90,                                                         
                                     92A-96, 99-109, 111-                                                       
                                     115.                                                                       
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    The modification shall be done in accordance with Airbus Service 
Bulletin A300-53-192, Revision 7, dated July 13, 1992, which 
contains the following list of effective pages:

------------------------------------------------------------------------
                                  Revision                              
           Page No.             level shown       Date shown on page    
                                  on page                               
------------------------------------------------------------------------
1, 2, 107, 122................            7  July 13, 1992.             
3, 4, 21, 22, 41-54...........            5  April 11, 1991.            
5, 59.........................            4  September 25, 1990.        
6, 6A, 7, 8, 11-17, 23, 27,               1  July 24, 1989.             
 29, 30, 55-58, 60-92, 94-106,                                          
 108.                                                                   
9, 10, 18-20, 24-26, 28, 93,              3  February 5, 1990.          
 31-40, 110-114, 116-121.                                               
109, 115......................            6  February 25, 1992.         
------------------------------------------------------------------------

    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.
    (k) This amendment becomes effective on June 27, 1997.

    Issued in Renton, Washington, on May 12, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-12859 Filed 5-22-97; 8:45 am]
BILLING CODE 4910-13-U