Airworthiness Directives; Aerospatiale Model ATR42 and ATR72 Series Airplanes

[Federal Register Volume 63, Number 152 (Friday, August 7, 1998)]
[Rules and Regulations]
[Pages 42222-42223]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-21102]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-146-AD; Amendment 39-10698; AD 98-16-21]
RIN 2120-AA64


Airworthiness Directives; Aerospatiale Model ATR42 and ATR72 
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 Aerospatiale Model ATR42 and ATR72 series 
airplanes, that requires one-time inspections to verify the correct 
shape of the stiffeners for the upper engine cowl and to detect wear of 
the aft upper fittings of the rear engine mounts, and corrective 
actions, if necessary. This amendment is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by this AD are intended 
to prevent wear (scratches or grooving) of the aft upper fittings of 
the rear engine mount, and consequent reduced structural integrity of 
the engine mounts.

DATES: Effective September 11, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 11, 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 
and ATR72 series airplanes was published in the Federal Register on 
June 12, 1998 (63 FR 32152). That action proposed to require one-time 
inspections to verify the correct shape of the stiffeners for the upper 
engine cowl and to detect wear of the aft upper fittings of the rear 
engine mounts, and corrective actions, if necessary.

Comments

    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 152 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 15 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the cost impact of 
the AD on U.S. operators is estimated to be $136,800, or $900 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.

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:

98-16-21 Aerospatiale: Amendment 39-10698. Docket 98-NM-146-AD.

    Applicability: Model ATR42 and Model ATR72 series airplanes, as 
listed in Avions de Transport Regional Service Bulletins ATR42-54-
0019 (for Model ATR42 series airplanes) and ATR72-54-1011 (for Model 
ATR72 series airplanes), both dated March 9, 1998; certificated in 
any category.


[[Page 42223]]


    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 prevent wear (scratches or grooving) of the aft upper 
fittings of the rear engine mount, and consequent reduced structural 
integrity of the engine mounts, accomplish the following:
    (a) Within 10 months after the effective date of this AD, 
perform a one-time visual inspection of the stiffeners for the upper 
left and right engine cowls to ensure the stiffeners have the 
correct lower edge profile, in accordance with the Accomplishment 
Instructions of Avions de Transport Regional Service Bulletin ATR42-
54-0019 or ATR72-54-1011, both dated March 9, 1998, as applicable.
    (1) If the lower edge profile of the stiffener meets the 
specifications of the applicable service bulletin, no further action 
is required by this paragraph.
    (2) If the lower edge profile of the stiffener does not meet the 
specifications of the applicable service bulletin, prior to further 
flight, modify or replace the stiffener with a new stiffener in 
accordance with the applicable service bulletin.
    (b) Within 10 months after the effective date of this AD, 
perform a one-time detailed visual inspection for wear (scratches or 
grooving) of the aft upper fittings of the left-and right-hand rear 
engine mounts, in accordance with Avions de Transport Regional 
Service Bulletin ATR42-54-0019 (for Model ATR42 series airplanes) or 
ATR72-54-1011 (for Model ATR72 series airplanes), both dated March 
9, 1998, as applicable.
    (1) If no wear is detected, no further action is required by 
this paragraph.
    (2) If any wear is detected that cannot be removed with a Type I 
or II blend-out as described in the applicable service bulletin, 
prior to further flight, repair in accordance with a method approved 
by the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate.
    (3) If any wear other than that specified in paragraph (b)(2) of 
this AD is detected, prior to further flight, repair in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin.
    (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. 
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.

    (d) 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.
    (e) Except as provided by paragraph (b)(2) of this AD, the 
actions shall be done in accordance with Avions de Transport 
Regional Service Bulletin ATR42-54-0019, dated March 9, 1998, or 
Avions de Transport Regional Service Bulletin ATR72-54-1011, dated 
March 9, 1998, as applicable. 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, edex 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 3: The subject of this AD is addressed in French 
airworthiness directives 98-069-073(B) (for Model ATR42 series 
airplanes), dated February 11, 1998; and 98-071-035(B) (for Model 
ATR72 series airplanes), dated February 11, 1998, as revised by 
Erratum 98-071-35(B), dated February 25, 1998.
    (f) This amendment becomes effective on September 11, 1998.

    Issued in Renton, Washington, on July 31, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-21102 Filed 8-6-98; 8:45 am]
BILLING CODE 4910-13-U

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