[Federal Register Volume 63, Number 102 (Thursday, May 28, 1998)]
[Rules and Regulations]
[Pages 29096-29098]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-13821]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-172-AD; Amendment 39-10544; AD 98-11-19]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 and 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 certain Airbus Model A310 and A300-600 series airplanes, 
that requires a visual inspection to detect cracks in the aft mount 
beam assembly of the engine; and replacement of any cracked beam with a 
new beam or beam assembly. This amendment also requires a fluorescent 
penetrant inspection to detect cracks in the aft mount beam assembly of 
the engine, and various follow-on actions. This amendment is prompted 
by reports indicating that, apparently due to manufacturing defects 
during the forging process, cracking was found in two engine aft mount 
beams. The actions specified by this AD are intended to detect and 
correct such cracking, which could result in reduced structural 
integrity of the aft mount beam assembly of the engine.

DATES: Effective July 2, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 2, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, 400 Main Street, East Hartford, 
Connecticut 06108. 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 certain Airbus Model A310 and 
A300-600 series airplanes was published in the Federal Register on 
April 1, 1997 (62 FR 15439). That action proposed to require a visual 
inspection to detect cracks in the aft mount beam assembly of the 
engine; and replacement of any cracked beam with a new beam or beam 
assembly. That action also proposed to require a fluorescent penetrant 
inspection to detect cracks in the aft mount beam assembly of the 
engine, and various follow-on actions.

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.
    One commenter supports the proposed rule.
    One commenter requests that the proposed AD be revised to cite 
accomplishment of Pratt & Whitney Service Bulletin PW4MD11 A71-102, 
Revision 3, dated August 30, 1995, as an equivalent alternative to 
accomplishment of Pratt & Whitney Alert Service Bulletins PW4NAC A71-
149, Revision 1, dated August 30, 1995, and PW7R4 A71-129, Revision 1, 
dated August 30, 1995, as referenced in the proposed AD.
    The FAA concurs with the commenter's request to cite accomplishment 
of Pratt & Whitney Service Bulletin PW4MD11 A71-102, Revision 3, dated 
August 30, 1995, as an equivalent alternative to accomplishment of 
Pratt & Whitney Alert Service Bulletins PW4NAC A71-149, Revision 1, 
dated August 30, 1995 or PW7R4 A71-129, Revision 1, dated August 30, 
1995. Pratt & Whitney Alert Service Bulletins PW4NAC A71-149, Revision 
1, dated August 30, 1995, and PW7R4 A71-129, Revision 1, dated August 
30, 1995, contain a Note that states: ``Service Bulletins PW4NAC A71-
149 (PW4000/AI), PW7R4 A71-129 (JT9D-7R4/AI), and PW4MD11 A71-102 
(PW4000/DAC) have been issued to cover all aircraft. Accomplishment of 
any one of these Service Bulletins satisfies the same intent of the 
other two.'' The FAA has revised this final rule to reflect this change 
by adding a new Note to the AD.

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 operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 8 Airbus Model A310 and A300-600 series 
airplanes of U.S. registry will be affected by this AD.
    It will take approximately 2 work hours per airplane to accomplish 
the required visual inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the visual 
inspection required by this AD on U.S. operators is estimated to be 
$960, or $120 per airplane.
    It will take approximately 34 work hours per airplane to accomplish 
the required fluorescent penetrant inspection, at an average labor rate 
of

[[Page 29097]]

$60 per work hour. Based on these figures, the cost impact of the 
fluorescent penetrant inspection required by this AD on U.S. operators 
is estimated to be $16,320, or $2,040 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:
98-11-19  Airbus Industrie: Amendment 39-10544. Docket 96-NM-172-AD.

    Applicability: Model A310 and A300-600 series airplanes, 
equipped with Pratt & Whitney Model JT9D-7R4D1, JT9D-7R4E1, JT9D-
7R4H1, PW4151, PW4156A, or PW4158 engines; 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 (c) 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 cracking in the aft mount beam assembly of 
the engine, which could result in reduced structural integrity of 
the aft mount beam assembly, accomplish the following:
    (a) Within 500 flight hours after the effective date of this AD, 
perform a visual inspection to detect cracks in the aft mount beam 
assembly of the engine, in accordance with Part 1 of the 
Accomplishment Instructions of Pratt & Whitney Alert Service 
Bulletin PW7R4 A71-129, Revision 1, dated August 30, 1995, or Pratt 
& Whitney Alert Service Bulletin PW4NAC A71-149, Revision 1, dated 
August 30, 1995; as applicable.
    (1) If no crack is detected, no further action is required by 
this paragraph.
    (2) If any crack is detected, prior to further flight, replace 
the cracked beam with a new beam or beam assembly, in accordance 
with the applicable service bulletin.
    (b) Within 4,000 flight cycles after the effective date of this 
AD, perform a fluorescent penetrant inspection to detect cracks in 
the aft mount beam assembly of the engine, in accordance with Part 2 
of the Accomplishment Instructions of Pratt & Whitney Alert Service 
Bulletin PW7R4 A71-129, Revision 1, dated August 30, 1995, or Pratt 
& Whitney Alert Service Bulletin PW4NAC A71-149, Revision 1, dated 
August 30, 1995; as applicable.
    (1) If no crack is detected, prior to further flight, perform an 
eddy current inspection to detect cracks in the aft mount beam 
assembly of the engine, in accordance with the applicable service 
bulletin.
    (i) If no crack is detected, prior to further flight, reidentify 
the beam in accordance with the applicable service bulletin.
    (ii) If any crack is detected, prior to further flight, replace 
the cracked beam with a new beam or beam assembly, in accordance 
with the applicable service bulletin.
    (2) If any crack is detected, prior to further flight, replace 
the cracked beam with a new beam or beam assembly, in accordance 
with the applicable service bulletin.

    Note 2: Accomplishment of the actions required by paragraphs (a) 
and (b) of this AD in accordance with Pratt & Whitney Service 
Bulletin PW4MD11 A71-102, Revision 3, dated August 30, 1995, is 
considered to be acceptable for compliance with those paragraphs.

    (c) 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, 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.

    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.

    (d) 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.
    (e) The actions shall be done in accordance with the following 
Pratt & Whitney Alert Service Bulletins, which contain the following 
list of effective pages:

----------------------------------------------------------------------------------------------------------------
  Service bulletin referenced    Page number shown on     Revision level shown on                               
           and date                      page                       page                  Date shown on page    
----------------------------------------------------------------------------------------------------------------
PW7R4 A71-129, Revision 1,      1, 4, 12, 17-21, 23,    1..........................  August 30, 1995.           
 August 30, 1995.                25-32.                                                                         
                                2, 3, 5-11, 13-16, 22,  Original...................  May 30, 1995.              
                                 24.                                                                            
PW4NAC A71-149, Revision 1,     1, 2, 4, 12, 17-21 25-  1..........................  August 30, 1995.           
 August 30, 1995.                32.                                                                            
                                3, 5-11, 13-16 22-24..  Original...................  May 30, 1995.              
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[[Page 29098]]

    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 Pratt & Whitney, 400 Main 
Street, East Hartford, Connecticut 06108. 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 96-020-195(B), dated January 31, 1996.

    (f) This amendment becomes effective on July 2, 1998.

    Issued in Renton, Washington, on May 18, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-13821 Filed 5-27-98; 8:45 am]
BILLING CODE 4910-13-U