AD Amdt-39-10503

[Federal Register Volume 63, Number 82 (Wednesday, April 29, 1998)]
[Rules and Regulations]
[Pages 23381-23382]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-11068]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-303-AD; Amendment 39-10503; AD 98-09-22]
RIN 2120-AA64


Airworthiness Directives; Aerospatiale Model ATR42-200, -300, and 
-320 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Aerospatiale Model ATR42-200, -300, and -320 
series airplanes, that requires an inspection to detect fatigue 
cracking of the windshield frame structure, and modification of the 
windshield frame structure. This amendment is prompted by the issuance 
of mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by this AD are intended 
to prevent reduced structural integrity of the airplane resulting from 
fatigue cracking of the windshield frame structure.

DATES: Effective June 3, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 3, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 
03, 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 certain Aerospatiale Model ATR42-
200, -300, and -320 series airplanes was published in the Federal 
Register on February 19, 1998 (63 FR 8373). That action proposed to 
require an inspection to detect fatigue cracking of the windshield 
frame structure, and modification of the windshield frame structure.

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.
    The commenter supports the proposed rule.

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 as proposed.

Cost Impact

    The FAA estimates that 106 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 19 work hours per airplane to accomplish 
the required inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection required by 
this AD on U.S. operators is estimated to be $120,840, or $1,140 per 
airplane.
    It will take approximately 191 work hours per airplane to 
accomplish the required modification specified in Aerospatiale Service 
Bulletin ATR42-53-0093, Revision 1, dated February 19, 1996, at an 
average labor rate of $60 per work hour. Required parts will be 
provided by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of this modification on U.S. operators 
is estimated to be $11,460 per airplane.
    It will take approximately 281 work hours per airplane to 
accomplish the required modification specified in Aerospatiale Service 
Bulletin ATR42-53-0094, Revision 2, dated February 19, 1996, at an 
average labor rate of $60 per work hour. Required parts will be 
provided by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of this modification on U.S. operators 
is estimated to be $16,860 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:

98-09-22  Aerospatiale: Amendment 39-10503. Docket 97-NM-303-AD.

    Applicability: Model ATR42-200, -300, and -320 series airplanes, 
on which

[[Page 23382]]

Aerospatiale Modification 01392 has not been installed, 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 (b) 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 prevent reduced structural integrity of the airplane 
resulting from fatigue cracking of the windshield frame structure, 
accomplish the following:
    (a) Prior to the accumulation of 24,000 total flight cycles, or 
within 60 days after the effective date of this AD, whichever occurs 
later: Inspect to detect cracking of the windshield frame structure 
in accordance with Operation Description (B--Inspection) of the 
Accomplishment Instructions of Aerospatiale Service Bulletin ATR42-
53-0093, Revision 1, or ATR42-53-0094, Revision 2, both dated 
February 19, 1996.
    (1) If the inspection reveals no crack, or reveals cracking that 
does not exceed the specifications listed in Figure 6, Sheet 1, of 
Service Bulletin ATR42-53-0093, Revision 1, dated February 19, 1996: 
Prior to further flight, modify the windshield frame structure in 
accordance with either service bulletin.
    (2) If the inspection reveals any crack that exceeds the 
specifications in Figure 6, Sheet 1, of Service Bulletin ATR42-53-
0093, Revision 1, dated February 19, 1996, but does not exceed the 
cut-out areas specified in Figure 7, Sheet 1, of Service Bulletin 
ATR42-53-0094, Revision 2, dated February 19, 1996: Prior to further 
flight, modify the windshield frame structure in accordance with 
Service Bulletin 42-53-0094, Revision 2, dated February 19, 1996.
    (3) If the inspection reveals any crack that exceeds the cut-out 
areas specified in Figure 7, Sheet 1, of Service Bulletin ATR42-53-
0094, Revision 2, dated February 19, 1996: Prior to further flight, 
modify the windshield frame structure in accordance with a method 
approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.

    Note 2: Accomplishment of the modifications specified in ATR 
Service Bulletin ATR42-53-0093, Revision 1, or ATR42-53-0094, 
Revision 2, both dated February 19, 1996, is not equivalent to 
accomplishment of Aerospatiale Modification 01392. Therefore the 
ATR42 Time Limits Document inspection items with ``PRE MOD 1392'' 
effectivity are still applicable for airplanes modified by either of 
the previously described service bulletins.

    (b) 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.

    (c) 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.
    (d) The actions shall be done in accordance with the following 
Aerospatiale Service Bulletins, which contain the specified 
effective pages:

----------------------------------------------------------------------------------------------------------------
 Service bulletin referenced and                                Revision level                                  
               date                Page number shown on page     shown on page          Date shown on page      
----------------------------------------------------------------------------------------------------------------
ATR42-53-0093, Revision 1,         1-4, 13..................  1.................  February 19, 1996.            
 February 19, 1996.                                                                                             
                                    5-12, 14-41.............  Original..........  April 26, 1995.               
ATR42-53-0094, Revision 2,         1, 2, 8, 9, 16, 18, 39,    2.................  February 19, 1996.            
 February 19, 1996.                 40, 48, 53, 54.                                                             
                                   3, 4, 7, 10-15, 17, 19-    1.................  May 29, 1995.                 
                                    24, 26, 27, 29-32, 34-                                                      
                                    38, 47, 55, 56.                                                             
                                   5, 6, 25, 28, 33, 41-46,   Original..........  April 24, 1995                
                                    49-52.                                                                      
----------------------------------------------------------------------------------------------------------------

    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 Aerospatiale, 316 Route de 
Bayonne, 31060 Toulouse, Cedex 03, 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 95-126-061(B), dated June 21, 1995.

    (e) This amendment becomes effective on June 3, 1998.

    Issued in Renton, Washington, on April 21, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-11068 Filed 4-28-98; 8:45 am]
BILLING CODE 4910-13-U