[Federal Register Volume 64, Number 41 (Wednesday, March 3, 1999)]
[Rules and Regulations]
[Pages 10216-10218]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-5178]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

RIN 2120-AA64
[Docket No. 97-SW-14-AD; Amendment 39-11062; AD 99-05-14]


Airworthiness Directives; Eurocopter France Model SA. 315B, SA. 
316B, SA. 316C, SA. 319B, and SE. 3160 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Eurocopter France Model SA. 315B, SA. 316B, SA. 316C, SA. 
319B, and SE. 3160 helicopters, that requires inspecting the main rotor 
blade cuff attachment fitting in the area of the main rotor blade 
(blade) attachment bolts for cracks, and removing and replacing the 
blade if a crack is found. This amendment is prompted by a report of a 
crack in a blade cuff attachment fitting/spar assembly that was 
discovered during fatigue testing by the manufacturer. The actions 
specified by this AD are intended to prevent failure of a blade cuff 
attachment fitting at a bolt hole location, loss of a blade, and 
subsequent loss of control of the helicopter.

EFFECTIVE DATE: April 7, 1999.

FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, fax (817) 
222-5961.

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 Eurocopter France Model SA. 315B, 
SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters was published in 
the Federal Register on November 3, 1998 (63 FR 59252). That action 
proposed to require inspecting the blade cuff attachment fitting in the 
area of the blade attachment bolt holes

[[Page 10217]]

for cracks, and removing and replacing any blade in which a crack is 
found.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule with only minor editorial changes that will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.
    The FAA estimates that 83 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 2 work hours per 
helicopter for the initial inspection and 2 work hours per helicopter 
for each repetitive inspection and that the average labor rate is $60 
per work hour. Required parts will cost approximately $40,000 per 
blade, if needed. Based on these figures, the total cost impact of the 
AD on U.S. operators is estimated to be $49,960 for one inspection and 
one blade replacement for each helicopter per year.
    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 FAA, Office of the Regional Counsel, 
Southwest Region, Attention: Rules Docket No. 97-SW-14-AD, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 a new airworthiness directive 
to read as follows:

AD 99-05-14 Eurocopter France: Amendment 39-11062. Docket No. 97-SW-
14-AD.
    Applicability: Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and 
SE. 3160 helicopters, with a main rotor blade, part number (P/N) 
3160S.11.10.000, 3160S.11.30.000, 3160S.11.35.000, 3160S.11.40.000, 
3160S.11.45.000, 3160S.11.50.000, or 3160S.11.55.000, installed, 
certificated in any category.

    Note 1: This AD applies to each helicopter 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 helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (c) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition, or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any helicopter from the applicability of this AD.
    Compliance: (1) For blades with less than 400 hours time-in-
service (TIS), required prior to the accumulation of 400 hours TIS, 
unless accomplished previously, and thereafter at intervals not to 
exceed 400 hours TIS; or (2) for blades with 400 hours or more TIS, 
required within 50 hours TIS or 30 calendar days after the effective 
date of this AD, whichever occurs first, unless accomplished 
previously, and thereafter at intervals not to exceed 400 hours TIS:
    To prevent failure of a main rotor blade (blade) cuff attachment 
fitting at a bolt hole location, loss of a blade, and subsequent 
loss of control of the helicopter, accomplish the following:
    (a) Inspect both upper and lower blade surfaces of each blade 
cuff for cracks (see Figure 1) as follows:
    (1) Use a mild liquid detergent or equivalent to remove all dirt 
from the blade cuff.
    (2) Inspect the blade cuff for cracks, paying particular 
attention to the area around the attaching bolts, using a 10-power 
or higher magnifying glass.
    (3) If a crack is suspected, remove any paint and clean the area 
under inspection using a Naptha-type solvent or equivalent, and 
conduct a dye penetrant inspection. Completely isolate the area 
under inspection with self-adhesive aluminum tape to prevent solvent 
or penetrating dye seepage into the other areas of the blade.
    (b) If a crack is detected, remove the blade and replace it with 
an airworthy blade.

[[Page 10218]]

[GRAPHIC] [TIFF OMITTED] TR03MR99.004


      
    (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, Rotorcraft Standards Staff, 
Rotorcraft Directorate, FAA. Operators shall submit their requests 
through an FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Standards Staff.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (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 helicopter to a location where 
the requirements of this AD can be accomplished.
    (e) This amendment becomes effective on April 7, 1999.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 96-081-036(B)R1, and AD 
96-082-054(B)R1, both dated April 24, 1996.

    Issued in Fort Worth, Texas, on February 24, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-5178 Filed 3-2-99; 8:45 am]
BILLING CODE 4910-13-U