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[Federal Register Volume 77, Number 112 (Monday, June 11, 2012)]
[Proposed Rules]
[Pages 34281-34283]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14037]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0602; Directorate Identifier 2009-SW-061-AD]
RIN 2120-AA64

Airworthiness Directives; Schweizer Aircraft Corporation

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) for Schweizer Aircraft Corporation (Schweizer) Model 269D and 
Model 269D Configuration A helicopters. The type certificate for these 
models is currently held by Sikorsky Aircraft Corporation (Sikorsky). 
This proposal is prompted by reports of loose horizontal stabilizers 
and cracks in the stabilizer-support structure for the extruded 
tailboom. The AD would require inspecting the aft fuselage assembly in 
the area around the attachment point of the horizontal stabilizer, 
including the paint, for a crack. This AD also would require inspecting 
the tailboom interior support structure, and if necessary, installing 
an inspection panel kit in the aft fuselage assembly, and installing 
doublers in the stabilizer support brackets. The actions specified by 
the proposed AD are intended to prevent separation of the horizontal 
stabilizer from the helicopter and subsequent loss of control of the 
helicopter.

DATES: We must receive comments on this proposed AD by August 10, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the economic 
evaluation, any comments received, and other information. The street 
address for the Docket Operations Office (telephone 800-647-5527) is in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.
    For service information identified in this proposed AD, contact 
Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical 
Support, mailstop s581a, 6900 Main Street, Stratford, CT 06614; 
telephone (800) 562-4409; email tsslibrary@sikorsky.com; or at http://www.sikorsky.com. You may review copies of the referenced service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Stephen Kowalski, Aviation Safety 
Engineer, New York Aircraft Certification Office, Engine & Propeller 
Directorate, 1600 Stewart Ave. suite 410, Westbury, NY 11590; telephone 
(516) 228-7327; email stephen.kowalski@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    This document proposes adopting a new AD for the Schweizer Model 
269D and Model 269D Configuration A helicopters, serial numbers 0001 to 
0062A, with aft fuselage assembly part number (P/N) 269D3300-1 
installed. This proposal is prompted by reports of loose horizontal 
stabilizers and cracks in the support structure for the extruded 
tailboom. The actions specified by the proposed AD are intended to 
prevent separation of the horizontal stabilizer from the helicopter and 
subsequent loss of control of the helicopter.

FAA's Determination

    We are proposing this AD because we evaluated all known relevant 
information and determined that an unsafe condition exists and is 
likely to exist or develop on other products of the same type design.

Related Service Information

    We have reviewed Schweizer Service Bulletin DB-018.3, dated 
December 13, 2007 (SB), which specifies inspecting for cracks in the 
fuselage assemblies and installing an inspection panel kit and 
stabilizer mount doublers. The Type Certificate for these helicopters 
transferred from Schweizer to Sikorsky on September 26, 2011.

[[Page 34282]]

Proposed AD Requirements

    This proposed AD would require:
     Before the first flight of each day, visually inspecting 
the aft fuselage assembly in the area around the attachment point of 
the horizontal stabilizer for a crack.
     If there is a crack in the aft fuselage assembly clip, aft 
bulkhead, or adjacent skins, repairing the crack and either performing 
a repetitive inspection at intervals not to exceed 200 hours time-in-
service (TIS) or replacing the aft fuselage assembly.
     If there is a crack in a longeron, tailboom tube collar or 
a forward stabilizer bulkhead, replacing the aft fuselage assembly.
     Within 100 hours TIS or three months, whichever occurs 
first:
    [cir] Removing the horizontal stabilizer, cleaning the horizontal 
stabilizer mounting brackets, inspecting the mounting brackets for wear 
greater than 0.002-inch deep, and replacing the mounting bracket if the 
bracket wear exceeds 0.002-inch deep.
    [cir] Modifying the aft fuselage assembly by installing Inspection 
Panel kit P/N SA-269DK-035, installing doublers on the forward side of 
each mounting bracket, inspecting the horizontal stabilizer forward and 
aft spars for wear in the mounting attachment areas, and replacing the 
spar if the wear exceeds 0.002-inch deep.
    [cir] Inspecting for rivet interference between the rivet heads and 
skin on the top surface of the horizontal stabilizer and the tailboom 
stiffening web near Station 232.4 and replacing the rivets if 
interference exists.
    [cir] Installing an airworthy horizontal stabilizer using 4 bolts, 
P/N NAS1304-4, and 4 washers, P/N AN960KD416 or NAS1149D0463K.
     Removing aft fuselage assembly P/N 269D3300-1, and 
replacing it with aft fuselage assembly P/N 269D3300-35, would be 
terminating action for the requirements of this AD.

Differences Between This Proposed AD and the Service Information

    The Schweizer SB requires contacting the manufacturer if certain 
damage is found for repair instructions. This AD does not.

Costs of Compliance

    We estimate that this proposed AD would affect 18 helicopters. The 
average labor rate is $85 per work hour. Based on these assessments, we 
estimate the following costs:
     Daily visual inspection. This would take about 10 minutes 
for a labor cost of $9. Assuming 365 daily inspections per year, the 
annual labor cost per helicopter would be about $3,285. The annual cost 
for the U.S. fleet would total $59,130.
     Internal inspection. This would take two work-hours for a 
labor cost of $170. Assuming 10 inspections a year, the annual labor 
cost per helicopter would be $1,700.
     Install inspection panel. This would take 16 work-hours 
for a labor cost of $1,360. Parts would cost $150 for a cost per 
helicopter of $1,510.
     Repair damaged longerons, tailboom tube collars, or 
forward stabilizer bulkhead as needed. This would take 24 work-hours 
for a labor cost of $2,040. Parts would cost $38,000 for a cost per 
helicopter of $40,040.
     Repair a crack in the aft fuselage assembly clip, aft 
bulkhead, or adjacent skins. This would take 24 work-hours for a labor 
cost of $2,040. Parts would cost $120 for a cost per helicopter of 
$2,160.
     Repair interference between the rivet heads and skin . 
This would take 10 work-hours for a labor cost of $850. No parts would 
be needed.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect 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.
    For the reasons discussed, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new 
Airworthiness Directive

(AD): SCHWEIZER AIRCRAFT CORPORATION HELICOPTERS: Docket No. FAA-
2012-0602; Directorate Identifier 2009-SW-061-AD.

(a) Applicability

    This AD applies to Schweizer Aircraft Corporation (Schweizer) 
Model 269D and Model 269D Configuration A helicopters, serial 
numbers 0001 to 0062A, with aft fuselage assembly part number (P/N) 
269D3300-1 installed, certificated in any category.
    Note to Applicability: The type certificate for these models is 
currently held by Sikorsky Aircraft Corporation.

(b) Unsafe Condition

    This AD defines the unsafe condition as loose horizontal 
stabilizers and cracks in the stabilizer support structure for the 
extruded tailboom, which could result in separation of the 
horizontal stabilizer from the helicopter and subsequent loss of 
helicopter control.

(c) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

[[Page 34283]]

(d) Required Actions

    (1) Before the first flight of each day, visually inspect the 
aft fuselage assembly in the area around the attachment point of the 
horizontal stabilizer, including the paint, for a crack. If there is 
a crack, remove the horizontal stabilizer and perform an interior 
inspection in accordance with Part II: Internal Inspection, 
paragraphs b. and c., of Schweizer Service Bulletin DB-018.3, dated 
December 13, 2007 (SB).
    (i) If there is a crack in the aft fuselage assembly clip, in 
the aft bulkhead, or in adjacent skins, repair the crack. 
Thereafter, at intervals not to exceed 200 hours time-in-service 
(TIS), remove the horizontal stabilizer and repeat the interior 
inspection in accordance with Part II: Internal Inspection, 
paragraphs b. and c., of the SB, or replace the aft fuselage 
assembly, P/N 269D3300-1,with an airworthy aft fuselage assembly, P/
N 269D3300-35.
    (ii) If there is a crack in a longeron, tailboom tube collar or 
a forward stabilizer bulkhead, replace the aft fuselage assembly 
with an airworthy aft fuselage assembly, P/N 269D3300-35.
    (2) Within 100 hours TIS or three months, whichever occurs 
first:
    (i) Remove the horizontal stabilizer, clean the horizontal 
stabilizer mounting brackets, and inspect the mounting brackets for 
wear greater than 0.002-inch deep. If the bracket wear exceeds 
0.002-inch deep, replace the mounting bracket with an airworthy 
mounting bracket.
    (ii) Modify the aft fuselage assembly by installing Inspection 
Panel kit P/N SA-269DK-035.
    (iii) Install doublers on the forward side of each mounting 
bracket in accordance with Part III-2, paragraphs e. through i., of 
the SB.
    (iv) Inspect the horizontal stabilizer forward and aft spars for 
wear in the mounting attachment areas. If the wear exceeds 0.002-
inch deep, replace the spar with an airworthy spar.
    (v) Inspect for rivet interference between the rivet heads and 
skin on the top surface of the horizontal stabilizer and the 
tailboom stiffening web near Station 232.4. If interference exists, 
replace with airworthy rivets.
    (vi) Install an airworthy horizontal stabilizer using 4 bolts, 
P/N NAS1304-4, and 4 washers, P/N AN960KD416 or NAS1149D0463K.
    (3) Removing aft fuselage assembly, P/N 269D3300-1, and 
replacing it with aft fuselage assembly, P/N 269D3300-35, is 
terminating action for the requirements of this AD.

(e) Special Flight Permit

    Special flight permits may be issued in accordance with 14 CFR 
21.197 and 21.199 provided that before operating the helicopter to a 
location to perform the actions in paragraphs (d)(1) through (d)(3) 
of this AD, a daily, pre-flight visual inspection is accomplished in 
accordance with paragraph (d)(1) of this AD.

(f) Alternative Methods of Compliance (AMOC)

    (1) The Manager, NYACO, FAA, may approve AMOCs for this AD. Send 
your proposal to: Stephen Kowalski, Aviation Safety Engineer, New 
York Aircraft Certification Office, Engine & Propeller Directorate, 
1600 Stewart Ave., suite 410, Westbury, NY 11590; telephone (516) 
228-7327; email stephen.kowalski@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(g) Additional Information

    For service information identified in this AD, contact Sikorsky 
Aircraft Corporation, Attn: Manager, Commercial Technical Support, 
mailstop s581a, 6900 Main Street, Stratford, CT 06614; telephone 
(800) 562-4409; email tsslibrary@sikorsky.com; or at http://www.sikorsky.com. You may review a copy of information at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft 
tailboom.

    Issued in Fort Worth, Texas, on May 25, 2012.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-14037 Filed 6-8-12; 8:45 am]
BILLING CODE 4910-13-P
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