Document ID: FAA-2012-0602-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Schweizer Aircraft Corporation
Posted Date: 2013-02-12T05:00Z

[Federal Register Volume 78, Number 29 (Tuesday, February 12, 2013)]
[Rules and Regulations]
[Pages 9789-9791]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-02583]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0602; Directorate Identifier 2009-SW-061-AD; 
Amendment 39-17338; AD 2013-03-04]
RIN 2120-AA64

Airworthiness Directives; Schweizer Aircraft Corporation

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the

[[Page 9790]]

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 AD 
requires 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 requires 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. This AD is prompted by reports of loose horizontal 
stabilizers and cracks in the stabilizer support structure for the 
extruded tailboom. The actions are intended to prevent separation of 
the horizontal stabilizer from the helicopter and subsequent loss of 
control of the helicopter.

DATES: This AD is effective March 19, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of March 19, 2013.

ADDRESSES: 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 the referenced service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

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 AD, any incorporated-by-reference 
service information, the economic evaluation, any comments received, 
and other information. The street address for the Docket Operations 
Office (phone: 800-647-5527) is U.S. Department of Transportation, 
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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:

Discussion

    On June 11, 2012, at 77 FR 34281, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 to include an AD that would apply to 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. That NPRM proposed to require inspecting the aft fuselage 
assembly in the area around the attachment point of the horizontal 
stabilizer, including the paint, for a crack. That AD also proposed 
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 proposed 
requirements were prompted by reports of loose horizontal stabilizers 
and cracks in the support structure of the extruded tailboom. The 
proposed requirements were intended to prevent separation of the 
horizontal stabilizer from the helicopter and subsequent loss of 
control of the helicopter.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (77 FR 34281, June 11, 
2012).

FAA's Determination

    We have reviewed the relevant information and determined that an 
unsafe condition exists and is likely to exist or develop on other 
products of these same type designs and that air safety and the public 
interest require adopting the AD requirements as proposed.

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.

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on

[[Page 9791]]

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 above, I certify that this AD:
    (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);
    (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 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2013-03-04 SCHWEIZER AIRCRAFT CORPORATION HELICOPTERS: Amendment 39-
17338; 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) Effective Date

    This AD becomes effective March 19, 2013.

(d) Compliance

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

(e) 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.

(f) Special Flight Permits

    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 (e)(1) through (e)(3) 
of this AD, a daily, pre-flight visual inspection is accomplished in 
accordance with paragraph (e)(1) of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, NY ACO, 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.

(h) Subject

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

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Schweizer Service Bulletin DB-018.3, dated December 13, 
2007.
    (ii) Reserved.
    (3) For Schweizer Aircraft Corporation 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.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on January 29, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-02583 Filed 2-11-13; 8:45 am]
BILLING CODE 4910-13-P