[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]
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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.
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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]
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