[Federal Register Volume 61, Number 6 (Tuesday, January 9, 1996)]
[Rules and Regulations]
[Pages 613-617]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-259]



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  Federal Register / Vol. 61, No. 6 / Tuesday, January 9, 1996 / Rules 
and Regulations  

[[Page 613]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-SW-33-AD; Amdt. 39-9484; AD 96-01-08]


Airworthiness Directives; Bell Helicopter Textron, A Division of 
Textron Canada Ltd. Model 222, 222B, 222U, and 230 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing priority letter 
airworthiness directive (AD) 95-23-02, applicable to certain serial-
numbered Bell Helicopter Textron, A Division of Textron Canada Ltd. 
(BHT) Model 222, 222B, 222U, and 230 helicopters, that currently 
requires an initial check of both surfaces of each tail rotor blade 
(blade) for cracks; an inspection of the blade skin if a crack of a 
specified size or location is found in the paint; and replacement of 
the blade if a crack is found in the blade skin. This AD requires the 
same actions as required by the priority letter AD, but corrects some 
affected serial numbers (S/N) that were incorrectly stated in that AD. 
This amendment is prompted by two incidents in which a crack developed 
in the stainless steel blade skins on BHT Model 230 helicopters, which 
are similar in design to the Models 222, 222B and 222U helicopters. The 
actions specified by this AD are intended to prevent failure of a blade 
due to a fatigue crack, loss of the tail rotor and tail rotor gear box, 
and subsequent loss of control of the helicopter.

DATES: Effective January 24, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before March 11, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 95-SW-33-AD, 2601 Meacham Blvd., room 663, Fort Worth, 
Texas 76137.

FOR FURTHER INFORMATION CONTACT: Mr. Charles Harrison, Aerospace 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
5960.

SUPPLEMENTARY INFORMATION: On November 3, 1995, the FAA issued priority 
letter AD 95-23-02, applicable to certain serial-numbered BHT Models 
222, 222B, 222U, and 230 helicopters, to require an initial check of 
both surfaces of each blade for cracks; an inspection of the blade skin 
if a crack of a specified size or location is found in the paint; and 
replacement of the blade if a crack is found in the blade skin. That 
action was prompted by two incidents in which a crack developed in the 
stainless steel blade skins on BHT Model 230 helicopters. In one of 
these incidents, the blade failed during flight. Subsequent 
investigation revealed fatigue cracks originating from sanding marks on 
the blade skin. The cracks were located just outboard of the stainless 
steel blade doubler. That condition, if not corrected, could result in 
failure of a blade due to a fatigue crack, loss of the tail rotor and 
tail rotor gear box, and subsequent loss of control of the helicopter.
    Since the issuance of that AD, the FAA has discovered that an error 
was made in the applicability paragraph of the priority letter AD, 
which incorrectly stated the S/N of one of the affected models. The 
Model 230 helicopters affected by the AD include S/N 23001 through 
23038. The priority letter AD incorrectly stated S/N 23001 through 
23034.
    Since the unsafe condition described is likely to exist or develop 
on other BHT Models 222, 222B, 222U, and 230 helicopters of the same 
type design, this AD supersedes priority letter AD 95-23-02 to require, 
before further flight, an initial visual check of both painted surfaces 
of each blade for cracks. If a crack of a specified size and location 
is found in the paint, removal of the paint and a visual inspection 
using a 10-power or higher magnifying glass is required before further 
flight. If this closer inspection reveals a crack in the blade skin, 
replacement of the blade with an airworthy blade is required. If no 
crack is found in the blade skin, the area from which the paint was 
removed is coated with a light-weight oil or an equivalent corrosion 
preventive compound, and then repetitive visual checks are required at 
intervals not to exceed 3 hours time-in-service (TIS). The initial 
visual check that is required before further flight and the repetitive 
checks may be performed by a pilot, but must be entered into the 
aircraft records showing compliance with paragraph (a) of this AD in 
accordance with sections 43.11 and 91.417(a)(2)(v) of the Federal 
Aviation Regulations. This AD allows a pilot to perform this check 
because it involves only a visual check for cracking in the painted 
surface of the blade skin, and can be performed equally well by a pilot 
or a mechanic.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for public 
comment hereon are impracticable, and that good cause exists for making 
this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before 

[[Page 614]]
and after the closing date for comments, in the Rules Docket for 
examination by interested persons. A report that summarizes each FAA-
public contact concerned with the substance of this AD will be filed in 
the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 95-SW-33-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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, 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 (AD), Amendment 39-9484, to read as follows:

AD 96-01-08  Bell Helicopter Textron, a Division of Textron Canada 
Ltd.: Amendment 39-9484. Docket No. 95-SW-33-AD. Supersedes Priority 
Letter AD 95-23-02, issued November 3, 1995, Docket No. 95-SW-31-AD.

    Applicability: Model 222 helicopters, serial numbers (S/N) 47006 
through 47089, and Model 222B helicopters, S/N 47131 through 47156, 
with tail rotor blades, part numbers (P/N) 222-016-001-101, -107, -
111, and -113; Model 222U helicopters, S/N 47501 through 47574, with 
tail rotor blades, P/N 222-016-001-107 and -111; and Model 230 
helicopters, S/N 23001 through 23038, with tail rotor blades, P/N 
222-016-001-111, 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 (g) 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: Required before further flight, unless accomplished 
previously. To prevent failure of a tail rotor blade (blade) due to 
a fatigue crack (see Figure 1), loss of the tail rotor and tail 
rotor gear box, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Clean the painted surfaces of the blades in an area 
approximately 6 inches spanwise on either side of the doubler tip. 
Visually check both surfaces of each blade for cracks by pushing the 
blade tip away from the surface being checked until it contacts the 
flapping stop and then holding the blade firmly against the stop. 
Pay particular attention to the area reaching from the doubler tip 
to 1 inch outboard, centering on an area 2 inches aft of the blade 
leading edge (see Figure 2).
    (b) The visual check required by paragraph (a) may be performed 
by an owner/operator (pilot) holding at least a private pilot 
certificate, and must be entered into the aircraft records showing 
compliance with paragraph (a) of this AD in accordance with sections 
43.11 and 91.417(a)(2)(v) of the Federal Aviation Regulations.
    (c) If the visual check described in paragraph (a) reveals any 
crack outboard of the doubler tip (Station 14.250), or any chordwise 
crack inboard of the doubler tip that is longer than 1 inch (see 
Figure 3), accomplish the following:
    (1) Remove the paint from the skin in the cracked area using the 
following procedures (see Figure 4):

    Note 2: Paint cracking that follows the contour of the doubler 
is common and is of no concern.

    (2) Using a 180 or 220 grit abrasion paper, sand by hand with 
spanwise strokes until greenish- or yellow-colored primer or bare 
metal begins to be exposed.
    (3) Using spanwise or circular sanding motions, continue hand-
sanding the remaining greenish- or yellow-colored primer in the 
cracked area using a 320 or 400 grit paper until sufficient metal 
has been exposed to allow inspection (see area indicated in Figure 
4).
    (d) Inspect the blade skin for cracks in the area that was 
exposed in accordance with paragraph (c) using a 10-power or higher 
magnifying glass.
    (1) If no crack is found in the blade skin, coat the bare metal 
area with a lightweight oil or an equivalent corrosion preventive 
compound.
    (2) If any crack is discovered, remove the blade and replace it 
with an airworthy blade.
    (e) Perform the requirements of this AD upon installation of a 
replacement blade.
    (f) Perform the visual checks of paragraph (a) of this AD and 
the subsequent inspections, if appropriate, at intervals not to 
exceed 3 hours TIS.

    Note 3: A lightweight oil or equivalent corrosion preventive 
compound may be applied after accomplishing the repetitive 
requirements of paragraph (f) of this AD.

    (g) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used when approved by the Manager, Rotorcraft Certification Office, 
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 Certification 
Office.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

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    (h) Special flight permits to accomplish the requirements of 
this AD will not be issued.
    (i) This amendment becomes effective on January 15, 1996.

    Issued in Fort Worth, Texas, on December 21, 1995.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-259 Filed 1-8-96; 8:45 am]
BILLING CODE 4910-13-U